Airworthiness Directive · Amendment 39-17903 · Fuselage main, structure
M7 Aerospace LLC Airplanes
This AD applies to the M7 Aerospace LLC airplanes listed in paragraphs (c)(1) through (c)(5) of this AD that are equipped with a bayonet shear pin main cabin door latching mechanism and are certificated in any category. Airplanes equipped with a “click-clack” main cabin door latching mechanism are not affected by this AD. Figure 3 of M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin CC7-53-005, and M7 Aerospace LLC SA227 Series Service Bulletin 227-53-009, both dated November 15, 2013, is a picture showing both styles of latching mechanisms.
(1) Model SA227-AT airplanes, serial numbers (S/Ns) AT570 through AT631, and AT695.
(2) Model SA227-AC airplanes, S/Ns AC570 through AC788.
(3) Model SA227-BC airplanes, S/Ns BC762, BC764, BC766, and BC770 through BC789.
(4) Model SA227-CC airplanes, S/N CC827, CC829, and CC840 through CC844.
(5) Model SA227-DC airplanes, S/Ns DC784, DC790 through DC826, DC828, DC830 through DC839, and DC845 through DC904.
We are adopting a new airworthiness directive (AD) for M7 Aerospace LLC Models SA227-AT, SA227-AC, SA227-BC, SA227-CC, and SA227- DC airplanes equipped with a bayonet shear pin main cabin door latching mechanism. This AD was prompted by fatigue cracks found in the internal door surround doubler, the fuselage external skin, and the door corner fittings at the fuselage upper forward corner of the main cabin door cutout. This AD requires repetitively inspecting the four corners of the main cabin door cutout for cracks, making necessary repairs, and reporting inspection results to M7 Aerospace LLC. We are issuing this AD to correct the unsafe condition on these products.
(1) Do the initial inspections of the fuselage upper forward corner and other 3 corners of the main cabin door cutout for cracks following Table 1 in Step 2. ACCOMPLISHMENT INSTRUCTIONS of M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin CC7-53-005 or M7 Aerospace LLC SA227 Series Service Bulletin 227-53-009, both dated November 15, 2013, as applicable. Do the inspections at the compliance times specified in paragraphs (g)(1)(i) through (g)(1)(iv) of this AD. For the purposes of this AD, owner/operators who do not track total aircraft flight cycles (TAC), use a.5 to 1 conversion, e.g., 35,000 TAC is equivalent to 17,500 hours time-in-service (TIS). For owner/operators who do not track flight cycles, use a 1 to 1 conversion, e.g., 300 flight cycles are equivalent to 300 hours TIS.
(i) For aircraft with more than 35,000 TAC, inspect within the next 300 flight cycles after August 27, 2014 (the effective date of this AD).
(ii) For aircraft with 20,001—35,000 TAC, inspect within the next 600 flight cycles after August 27, 2014 (the effective date of this AD).
(iii) For aircraft with 12,000—20,000 TAC, inspect within the next 1,000 flight cycles after August 27, 2014 (the effective date of this AD).
(iv) For aircraft with less than 12,000 TAC, inspect at 12,000 flight cycles or within the next 1,000 flight cycles after August 27, 2014 (the effective date of this AD), whichever occurs later.
(2) If no cracks are found during the inspections required by paragraph (g)(1) of this AD, repetitively thereafter at intervals not to exceed 2,000 flight cycles do the inspections of the fuselage upper forward corner and other 3 corners of the main cabin door cutout for cracks following Table 1 in Step 2. ACCOMPLISHMENT INSTRUCTIONS of M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin CC7-53-005 or M7 Aerospace LLC SA227 Series Service Bulletin 227-53-009, both dated November 15, 2013, as applicable.
(1) If any cracks are found during any inspection required in paragraph (g) through paragraph (i) of this AD, before further flight after the inspection in which a crack is found, repair or replace the cracked structure following Step 3. REPAIR OF CRACKED INNER DOUBLE, Step 4. REPAIR OF CRACKED FUSELAGE SKIN, and/or Step 5. REPAIR OF CRACKED CORNER FITTING of M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin CC7-53-005, or M7 Aerospace LLC SA227 Series Service Bulletin 227-53-009, both dated November 15, 2013, as applicable.
(2) If you made the repairs required in paragraph (h)(1) of this AD by installing repair kit drawing 27K24191-001, do the threshold and repeat inspections following Table 2 in Step 2. ACCOMPLISHMENT INSTRUCTIONS of M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin CC7-53-005, dated November 15, 2013; or M7 Aerospace LLC SA227 Series Service Bulletin 227-53-009, dated November 15, 2013, as applicable.
(3) If you made the repairs required in paragraph (h)(1) of this AD by replacing the fuselage skin by installing repair kit drawing 27K24191-003, or if the corner fitting was replaced and no other cracks are present, repetitively thereafter inspect following Table 1 in Step 2. ACCOMPLISHMENT INSTRUCTIONS of M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin CC7-53-005, or M7 Aerospace LLC SA227 Series Service Bulletin 227-53-009, both dated November 15, 2013, as applicable.
After any inspection required in paragraph (g)(1) and (g)(2) of this AD and if no damage, defects, or cracks are found, you may install repair kit drawing 27K24191-001 following Step 6. ADDITION OF KIT DRAWING REPAIR MEMBERS AS PREVENTATIVE ACTION of M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin CC7-53-005, or M7 Aerospace LLC SA227 Series Service Bulletin 227-53-009, both dated November 15, 2013, as applicable, to extend the inspection intervals. After installing repair kit drawing 27K24191-001, do the threshold and repeat inspections following Table 3 of Step 2. ACCOMPLISHMENT INSTRUCTIONS of M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin CC7-53-005, or M7 Aerospace LLC SA227 Series Service Bulletin 227-53-009, both dated November 15, 2013, as applicable.
Within 30 days after any inspection required by paragraph (g) through paragraph (i) of this AD where a crack or any other damage is found, report the results of that inspection to M7 Aerospace LLC following the instructions specified in Step 2.I. of the ACCOMPLISHMENT INSTRUCTIONS of M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin CC7-53-005, dated November 15, 2013; or Step 2.J. of the ACCOMPLISHMENT INSTRUCTIONS of M7 Aerospace LLC SA227 Series Service Bulletin 227-53-009, dated November 15, 2013, as applicable.
As of August 27, 2014 (the effective date of this AD), owner/operators who had the an inspection and any resulting repairs done before the effective date of this AD using procedures different from those specified in M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin CC7-53-005, dated November 15, 2013; and M7 Aerospace LLC SA227 Series Service Bulletin 227-53-009, dated November 15, 2013, may apply for an alternative method of compliance (AMOC) following the instructions in paragraph (m) of this AD.
A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
