121.1111—Electrical wiring interconnection systems (EWIS) maintenance program.
This subpart prescribes rules for obtaining approval of areas and routes by certificate holders conducting supplemental operations.
Code of Federal Regulations
(a)
Except as provided in paragraph (f) of this section, this section applies to transport category, turbine-powered airplanes with a type certificate issued after January 1, 1958, that, as a result of original type certification or later increase in capacity, have—
(b)
After March 10, 2011, no certificate holder may operate an airplane identified in paragraph (a) of this section unless the maintenance program for that airplane includes inspections and procedures for electrical wiring interconnection systems (EWIS).
(c)
The proposed EWIS maintenance program changes must be based on EWIS Instructions for Continued Airworthiness (ICA) that have been developed in accordance with the provisions of Appendix H of part 25 of this chapter applicable to each affected airplane (including those ICA developed for supplemental type certificates installed on each airplane) and that have been approved by the FAA Oversight Office.
(1)
For airplanes subject to § 26.11 of this chapter, the EWIS ICA must comply with paragraphs H25.5(a)(1) and (b).
(2)
For airplanes subject to § 25.1729 of this chapter, the EWIS ICA must comply with paragraph H25.4 and all of paragraph H25.5.
(d)
After March 10, 2011, before returning an airplane to service after any alterations for which EWIS ICA are developed, the certificate holder must include in the airplane's maintenance program inspections and procedures for EWIS based on those ICA.
(e)
The EWIS maintenance program changes identified in paragraphs (c) and (d) of this section and any later EWIS revisions must be submitted to the Principal Inspector for review and approval.
(1) Lockheed L-188
(2) Bombardier CL-44
(3) Mitsubishi YS-11
(4) British Aerospace BAC 1-11
(5) Concorde
(6) deHavilland D.H. 106 Comet 4C
(7) VFW-Vereinigte Flugtechnische Werk VFW-614
(8) Illyushin Aviation IL 96T
(9) Bristol Aircraft Britannia 305
(10) Handley Page Herald Type 300
(11) Avions Marcel Dassault—Breguet Aviation Mercure 100C
(12) Airbus Caravelle
(13) Lockheed L-300
(a)
Except as provided in paragraph (g) of this section, this section applies to transport category, turbine-powered airplanes with a type certificate issued after January 1, 1958, that, as a result of original type certification or later increase in capacity, have—
(b)
For each airplane on which an auxiliary fuel tank is installed under a field approval, before June 16, 2008, the certificate holder must submit to the FAA Oversight Office proposed maintenance instructions for the tank that meet the requirements of Special Federal Aviation Regulation No. 88 (SFAR 88) of this chapter.
(c)
After December 16, 2008, no certificate holder may operate an airplane identified in paragraph (a) of this section unless the maintenance program for that airplane has been revised to include applicable inspections, procedures, and limitations for fuel tanks systems.
(d)
The proposed fuel tank system maintenance program revisions must be based on fuel tank system Instructions for Continued Airworthiness (ICA) that have been developed in accordance with the applicable provisions of SFAR 88 of this chapter or § 25.1529 and part 25, Appendix H, of this chapter, in effect on June 6, 2001 (including those developed for auxiliary fuel tanks, if any, installed under supplemental type certificates or other design approval) and that have been approved by the FAA Oversight Office.
(e)
After December 16, 2008, before returning an aircraft to service after any alteration for which fuel tank ICA are developed under SFAR 88 or under § 25.1529 in effect on June 6, 2001, the certificate holder must include in the maintenance program for the airplane inspections and procedures for the fuel tank system based on those ICA.
(f)
The fuel tank system maintenance program changes identified in paragraphs (d) and (e) of this section and any later fuel tank system revisions must be submitted to the Principal Inspector for review and approval.
(1) Bombardier CL-44
(2) Concorde
(3) deHavilland D.H. 106 Comet 4C
(4) VFW-Vereinigte Flugtechnische Werk VFW-614
(5) Illyushin Aviation IL 96T
(6) Bristol Aircraft Britannia 305
(7) Handley Page Herald Type 300
(8) Avions Marcel Dassault—Breguet Aviation Mercure 100C
(9) Airbus Caravelle
(10) Lockheed L-300
(a) Applicability.
This section applies to certificate holders operating any transport category, turbine-powered airplane with a maximum takeoff gross weight greater than 75,000 pounds and a type certificate issued after January 1, 1958, regardless of whether the maximum takeoff gross weight is a result of an original type certificate or a later design change. This section also applies to certificate holders operating any transport category, turbine-powered airplane with a type certificate issued after January 1, 1958, regardless of the maximum takeoff gross weight, for which a limit of validity of the engineering data that supports the structural maintenance program (hereafter referred to as LOV) is required in accordance with § 25.571 or § 26.21 of this chapter after January 14, 2011.
(b) Limit of validity.
No certificate holder may operate an airplane identified in paragraph (a) of this section after the applicable date identified in Table 1 of this section unless an Airworthiness Limitations section approved under Appendix H to part 25 or § 26.21 of this chapter is incorporated into its maintenance program. The ALS must—
(1)
Include an LOV approved under § 25.571 or § 26.21 of this chapter, as applicable, except as provided in paragraph (f) of this section; and
(c) Operation of airplanes excluded from
No certificate holder may operate an airplane identified in § 26.21(g) of this chapter after July 14, 2013, unless an Airworthiness Limitations section approved under Appendix H to part 25 or § 26.21 of this chapter is incorporated into its maintenance program. The ALS must—
(1)
Include an LOV approved under § 25.571 or § 26.21 of this chapter, as applicable, except as provided in paragraph (f) of this section; and
(d) Extended limit of validity.
No certificate holder may operate an airplane beyond the LOV, or extended LOV, specified in paragraph (b)(1), (c), (d), or (f) of this section, as applicable, unless the following conditions are met:
(i)
Includes an extended LOV and any widespread fatigue damage airworthiness limitation items approved under § 26.23 of this chapter; and
(2)
The extended LOV and the airworthiness limitation items pertaining to widespread fatigue damage must be clearly distinguishable within its maintenance program.
(e) Principal Maintenance Inspector approval.
Certificate holders must submit the maintenance program revisions required by paragraphs (b), (c), and (d) of this section to the Principal Maintenance Inspector for review and approval.
(f) Exception.
For any airplane for which an LOV has not been approved as of the applicable compliance date specified in paragraph (c) or Table 1 of this section, instead of including an approved LOV in the ALS, an operator must include the applicable default LOV specified in Table 1 or Table 2 of this section, as applicable, in the ALS.
| Airplane model | Compliance date—months afterJanuary 14, 2011 | Default LOV[flight cycles (FC)or flight hours (FH)] |
|---|---|---|
| Airbus—Existing1 Models Only: | ||
| A300 B2-1A, B2-1C, B2K-3C, B2-203 | 30 | 48,000 FC |
| A300 B4-2C, B4-103 | 30 | 40,000 FC |
| A300 B4-203 | 30 | 34,000 FC |
| A300-600 Series | 30 | 30,000 FC/67,500 FH |
| A310-200 Series | 30 | 40,000 FC/60,000 FH |
| A310-300 Series | 30 | 35,000 FC/60,000 FH |
| A318 Series | 60 | 48,000 FC/60,000 FH |
| A319 Series | 60 | 48,000 FC/60,000 FH |
| A320-100 Series | 60 | 48,000 FC/48,000 FH |
| A320-200 Series | 60 | 48,000 FC/60,000 FH |
| A321 Series | 60 | 48,000 FC/60,000 FH |
| A330-200, -300 Series (except WV050 family) (non enhanced) | 60 | 40,000 FC/60,000 FH |
| A330-200, -300 Series WV050 family (enhanced) | 60 | 33,000 FC/100,000 FH |
| A330-200 Freighter Series | 60 | See NOTE. |
| A340-200, -300 Series (except WV 027 and WV050 family) (non enhanced) | 60 | 20,000 FC/80,000 FH |
| A340-200, -300 Series WV 027 (non enhanced) | 60 | 30,000 FC/60,000 FH |
| A340-300 Series WV050 family (enhanced) | 60 | 20,000 FC/100,000 FH |
| A340-500, -600 Series | 60 | 16,600 FC/100,000 FH |
| A380-800 Series | 72 | See NOTE. |
| Boeing—Existing1 Models Only: | ||
| 717 | 60 | 60,000 FC/60,000 FH |
| 727 (all series) | 30 | 60,000 FC |
| 737 (Classics): 737-100, -200, -200C, -300, -400, -500 | 30 | 75,000 FC |
| 737 (NG): 737-600, -700, -700C, -800, -900, -900ER | 60 | 75,000 FC |
| 747 (Classics): 747-100, -100B, -100B SUD, -200B, -200C, -200F, -300, 747SP, 747SR | 30 | 20,000 FC |
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| 747-400: 747-400, -400D, -400F | 60 | 20,000 FC |
| 757 | 60 | 50,000 FC |
| 767 | 60 | 50,000 FC |
| 777-200, -300 | 60 | 40,000 FC |
| 777-200LR, 777-300ER | 72 | 40,000 FC |
| 777F | 72 | 11,000 FC |
| Bombardier—Existing1 Models Only: | ||
| CL-600: 2D15 (Regional Jet Series 705), 2D24 (Regional Jet Series 900) | 72 | 60,000 FC |
| Embraer—Existing1 Models Only: | ||
| ERJ 170 | 72 | See NOTE. |
| ERJ 190 | 72 | See NOTE. |
| Fokker—Existing1 Models Only: | ||
| F.28 Mark 0070, Mark 0100 | 30 | 90,000 FC |
| Lockheed—Existing1 Models Only: | ||
| L-1011 | 30 | 36,000 FC |
| 188 | 30 | 26,600 FC |
| 382 (all series) | 30 | 20,000 FC/50,000 FH |
| McDonnell Douglas—Existing1 Models Only: | ||
| DC-8, -8F | 30 | 50,000 FC/50,000 FH |
| DC-9 (except for MD-80 models) | 30 | 100,000 FC/100,000 FH |
| MD-80 (DC-9-81, -82, -83, -87, MD-88) | 30 | 50,000 FC/50,000 FH |
| MD-90 | 60 | 60,000 FC/90,000 FH |
| DC-10-10, -15 | 30 | 42,000 FC/60,000 FH |
| DC-10-30, -40, -10F, -30F, -40F | 30 | 30,000 FC/60,000 FH |
| MD-10-10F | 60 | 42,000 FC/60,000 FH |
| MD-10-30F | 60 | 30,000 FC/60,000 FH |
| MD-11, MD-11F | 60 | 20,000 FC/60,000 FH |
| Maximum Takeoff Gross Weight Changes: | ||
| All airplanes whose maximum takeoff gross weight has been decreased to 75,000 pounds or below after January 14, 2011 or increased to greater than 75,000 pounds at any time by an amended type certificate or supplemental type certificate | 30, or within 12 months after the LOV is approved, or before operating the airplane, whichever occurs latest | Not applicable. |
| All Other Airplane Models (TCs and amended TCs) not Listed in Table 2 | 72, or within 12 months after the LOV is approved, or before operating the airplane, whichever occurs latest | Not applicable. |
| 1 Type certificated as of January 14, 2011. | ||
Code of Federal Regulations
| Airplane model | Default LOV[flight cycles (FC)or flight hours (FH)] |
|---|---|
| Airbus: | |
| Caravelle | 15,000 FC/24,000 FH |
| Avions Marcel Dassault: | |
| Breguet Aviation Mercure 100C | 20,000 FC/16,000 FH |
| Boeing: | |
| Boeing 707 (-100 Series and -200 Series) | 20,000 FC |
| Boeing 707 (-300 Series and -400 Series) | 20,000 FC |
| Boeing 720 | 30,000 FC |
| Bombardier: | |
| CL-44D4 and CL-44J | 20,000 FC |
| BD-700 | 15,000 FH |
| Bristol Aeroplane Company: | |
| Britannia 305 | 10,000 FC |
| British Aerospace Airbus, Ltd.: | |
| BAC 1-11 (all models) | 85,000 FC |
| British Aerospace (Commercial Aircraft) Ltd.: | |
| Armstrong Whitworth Argosy A.W. 650 Series 101 | 20,000 FC |
| BAE Systems (Operations) Ltd.: | |
| BAe 146-100A (all models) | 50,000 FC |
| BAe 146-200-07 | 50,000 FC |
|
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| BAe 146-200-07 Dev | 50,000 FC |
| BAe 146-200-11 | 50,000 FC |
| BAe 146-200-07A | 47,000 FC |
| BAe 146-200-11 Dev | 43,000 FC |
| BAe 146-300 (all models) | 40,000 FC |
| Avro 146-RJ70A (all models) | 40,000 FC |
| Avro 146-RJ85A and 146-RJ100A (all models) | 50,000 FC |
| D & R Nevada, LLC: | |
| Convair Model 22 | 1,000 FC/1,000 FH |
| Convair Model 23M | 1,000 FC/1,000 FH |
| deHavilland Aircraft Company, Ltd.: | |
| D.H. 106 Comet 4C | 8,000 FH |
| Gulfstream: | |
| GV | 40,000 FH |
| GV-SP | 40,000 FH |
| Ilyushin Aviation Complex: | |
| IL-96T | 10,000 FC/30,000 FH |
| Lockheed: | |
| 300-50A01 (USAF C 141A) | 20,000 FC |
Code of Federal Regulations
Code of Federal Regulations
(a) Applicability.
Except as provided in paragraph (o) of this section, this section applies to transport category, turbine-powered airplanes with a type certificate issued after January 1, 1958, that, as a result of original type certification or later increase in capacity have:
(b) New Production Airplanes.
Except in accordance with § 121.628, no certificate holder may operate an airplane identified in Table 1 of this section (including all-cargo airplanes) for which the State of Manufacture issued the original certificate of airworthiness or export airworthiness approval after December 27, 2010 unless an Ignition Mitigation Means (IMM) or Flammability Reduction Means (FRM) meeting the requirements of § 26.33 of this chapter is operational.
| Model—Boeing | Model—Airbus |
|---|---|
| 747 Series | A318, A319, A320, A321 Series |
| 737 Series | A330, A340 Series |
| 777 Series | |
| 767 Series |
(c) Auxiliary Fuel Tanks.
After the applicable date stated in paragraph (e) of this section, no certificate holder may operate any airplane subject to § 26.33 of this chapter that has an Auxiliary Fuel Tank installed pursuant to a field approval, unless the following requirements are met:
(1)
The certificate holder complies with 14 CFR 26.35 by the applicable date stated in that section.
(2)
The certificate holder installs Flammability Impact Mitigation Means (FIMM), if applicable, that is approved by the FAA Oversight Office.
(d) Retrofit.
Except as provided in paragraphs (j), (k), and (l) of this section, after the dates specified in paragraph (e) of this section, no certificate holder may operate an airplane to which this section applies unless the requirements of paragraphs (d)(1) and (d)(2) of this section are met.
(1)
IMM, FRM or FIMM, if required by §§ 26.33, 26.35, or 26.37 of this chapter, that are approved by the FAA Oversight Office, are installed within the compliance times specified in paragraph (e) of this section.
(e) Compliance Times.
Except as provided in paragraphs (k) and (l) of this section, the installations required by paragraph (d) of this section must be accomplished no later than the applicable dates specified in paragraph (e)(1), (e)(2), or (e)(3) of this section.
(1)
Fifty percent of each certificate holder's fleet identified in paragraph (d)(1) of this section must be modified no later than December 26, 2014.
(2)
One hundred percent of each certificate holder's fleet identified in paragraph (d)(1) of this section must be modified no later than December 26, 2017.
(3)
For those certificate holders that have only one airplane of a model identified in Table 1 of this section, the airplane must be modified no later than December 26, 2017.
(1)
Operate an airplane on which IMM or FRM has been installed before the dates specified in paragraph (e) of this section unless the IMM or FRM is operational, or
(2)
Deactivate or remove an IMM or FRM once installed unless it is replaced by a means that complies with paragraph (d) of this section.
(g) Maintenance Program Revisions.
No certificate holder may operate an airplane for which airworthiness limitations have been approved by the FAA Oversight Office in accordance with §§ 26.33, 26.35, or 26.37 of this chapter after the airplane is modified in accordance with paragraph (d) of this section unless the maintenance program for that airplane is revised to include those applicable airworthiness limitations.
(h)
After the maintenance program is revised as required by paragraph (g) of this section, before returning an airplane to service after any alteration for which airworthiness limitations are required by §§ 25.981, 26.33, or 26.37 of this chapter, the certificate holder must revise the maintenance program for the airplane to include those airworthiness limitations.
(i)
The maintenance program changes identified in paragraphs (g) and (h) of this section must be submitted to the operator's Principal Maintenance Inspector responsible for review and approval prior to incorporation.
(j)
The requirements of paragraph (d) of this section do not apply to airplanes operated in all-cargo service, but those airplanes are subject to paragraph (f) of this section.
(k)
The compliance dates specified in paragraph (e) of this section may be extended by one year, provided that—
(1)
No later than March 26, 2009, the certificate holder notifies its assigned Flight Standards Office or Principal Inspector that it intends to comply with this paragraph;
(2)
No later than June 24, 2009, the certificate holder applies for an amendment to its operations specification in accordance with § 119.51 of this chapter and revises the manual required by § 121.133 to include a requirement for the airplane models specified in Table 2 of this section to use ground air conditioning systems for actual gate times of more than 30 minutes, when available at the gate and operational, whenever the ambient temperature exceeds 60 degrees Fahrenheit; and
(3)
Thereafter, the certificate holder uses ground air conditioning systems as described in paragraph (k)(2) of this section on each airplane subject to the extension.
| Model—Boeing | Model—Airbus |
|---|---|
| 747 Series | A318, A319, A320, A321 Series |
| 737 Series | A300, A310 Series |
| 777 Series | A330, A340 Series |
| 767 Series | |
| 757 Series |
(l)
For any certificate holder for which the operating certificate is issued after December 26, 2008, the compliance date specified in paragraph (e) of this section may be extended by one year, provided that the certificate holder meets the requirements of paragraph (k)(2) of this section when its initial operations specifications are issued and, thereafter, uses ground air conditioning systems as described in paragraph (k)(2) of this section on each airplane subject to the extension.
(m)
After the date by which any person is required by this section to modify 100 percent of the affected fleet, no certificate holder may operate in passenger service any airplane model specified in Table 2 of this section unless the airplane has been modified to comply with § 26.33(c) of this chapter.
(n)
No certificate holder may operate any airplane on which an auxiliary fuel tank is installed after December 26, 2017 unless the FAA has certified the tank as compliant with § 25.981 of this chapter, in effect on December 26, 2008.