Federal Register / Vol. 77, No. 89 / Tuesday, May 8, 2012 / Rules and Regulations 26937 

originating from the official 

establishment has entered commerce, if 

the official establishment believes or has 

reason to believe that this has 

happened. The official establishment 

must inform the District Office of the 

type, amount, origin, and destination of 

the adulterated or misbranded product. 

§ 418.3 Preparation and maintenance of 

written recall procedures. 

Each official establishment must 

prepare and maintain written 

procedures for the recall of any meat, 

meat food, poultry, or poultry product 

produced and shipped by the official 

establishment. These written procedures 

must specify how the official 

establishment will decide whether to 

conduct a product recall, and how the 

establishment will effect the recall, 

should it decide that one is necessary. 

§ 418.4 Records. 

All records, including records 

documenting procedures required by 

this part, must be available for official 

review and copying. 

Done in Washington, DC, on May 1, 2012. 

Alfred V. Almanza, 

Administrator. 

[FR Doc. 2012–10917 Filed 5–7–12; 8:45 am] 

BILLING CODE 3410–DM–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1066; Directorate 

Identifier 2011–NM–050–AD; Amendment 

39–16917; AD 2012–01–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain Airbus Model A300 B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and 

B4–203 airplanes; and Model A300 B4– 

601, B4–603, B4–620, B4–622, B4–605R, 

B4–622R, and F4–605R airplanes. That 

AD currently requires repetitive 

inspections for cracking in Gear Rib 5 of 

the main landing gear (MLG) attachment 

fittings at the lower flange, and repair if 

necessary; and provides an optional 

spot-facing modification around certain 

fastener holes, which would terminate 

certain repetitive inspections. This new 

AD mandates the optional spot-facing 

modification. This AD was prompted by 

new cases of cracks discovered during 

scheduled maintenance checks. We are 

issuing this AD to prevent cracking of 

the Gear Rib 5 right-hand and left-hand 

attachment fitting at the lower flanges of 

the MLG, which could result in failed 

bolts penetrating through the rear spar 

and into a fuel tank, consequent fuel 

loss, and reduced structural integrity of 

the airplane. 

DATES: This AD becomes effective June 

12, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 12, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of January 5, 2011 (75 FR 

74610, December 1, 2010). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of July 18, 2006 (71 FR 

33994, June 13, 2006). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of April 12, 2000 (65 FR 

12077, March 8, 2000). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of October 20, 1999 (64 FR 

49966, September 15, 1999). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on October 11, 2011 (76 FR 

62673), and proposed to supersede AD 

2010–23–26, Amendment 39–16516 (75 

FR 74610, December 1, 2010). That 

NPRM proposed to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Following the occurrence of cracks on the 

MLG [main landing gear] Rib 5 RH [righthand] and LH [left-hand] attachment fitting 

lower flanges, DGAC [Direction Ge ́ne ́rale de 

l’Aviation Civile] France AD 2003–318(B) 

was issued to require repetitive inspections 

and, as terminating action, the embodiment 

of Airbus Service Bulletins (SB) A300–57– 

0235 and A300–57–6088 * * *. 

Subsequently, new cases of cracks were 

discovered during scheduled maintenance 

checks by operators of A300B4 and A300– 

600 type aeroplanes on which the 

terminating action SB’s were embodied. This 

condition, if not corrected, could affect the 

structural integrity of those aeroplanes. 

To address and correct this condition, 

Airbus developed an inspection programme 

for aeroplanes modified in accordance with 

SB A300–57–0235 or A300–57–6088. This 

inspection programme was required to be 

implemented by DGAC France AD F–2005– 

113, original issue and later revision 1 

[parallel to part of FAA AD 2006–12–13, 

Amendment 39–14639 (71 FR 33994, June 

13, 2006)]. 

A new EASA [European Aviation Safety 

Agency] AD 2008–0111, superseding DGAC 

France AD F–2005–113R1, was issued to 

reduce the applicability. For aeroplanes 

already compliant with DGAC France AD F– 

2005–113R1, no further action was required. 

Since EASA AD 2008–0111 issuance, 

Airbus reviewed the inspection programmes 

of SB A300–57A0246 and SB A300–57A6101 

to introduce repetitive inspections including 

a new inspection technique for holes 47 and 

54 and to reduce inspections threshold and 

intervals from 700 Flight Cycles (FC) to 400 

FC until a revised terminating action is made 

available. 

For the reasons stated above, EASA AD 

2009–0081 superseded EASA AD 2008–0111 

and required operators to comply with the 

new inspection programme introduced in 

Revisions 3 of Airbus SB A300–57A0246 and 

Airbus SB A300–57A6101. 

EASA AD 2009–0081 R1 [which 

corresponds to FAA AD 2010–23–26, 

Amendment 39–16516 (75 FR 74610, 

December 1, 2010)] has been published to 

introduce an optional terminating action 

which consisted of spot-facing the sensitive 

holes of the MLG Rib 5 (LH and RH) bottom 

flanges. 

Later discussions with Airbus have 

demonstrated the necessity to require the 

spot-facing modification as a final solution 

(no longer optional). This new [EASA] AD 

retains the inspection requirements of EASA 

AD 2009–0081 R1, which is superseded, and 

requires the spot-facing of sensitive holes of 

the MLG Rib 5 (LH and RH) bottom flanges 

as terminating action. 

Required actions include repairing 

discrepancies (e.g., cracking or a second 

oversize or greater fastener hole). You 

may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. The 

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26938 Federal Register / Vol. 77, No. 89 / Tuesday, May 8, 2012 / Rules and Regulations 

commenter supports the NPRM (76 FR 

62673, October 11, 2011). 

Explanation of Changes Made to This 

AD 

We have made the following changes 

to this AD. These changes have not 

changed the intent of any provisions 

specified in this AD. 

• Revised certain headers throughout 

this AD. 

• Redesignated Notes 1, 2, and 3 of 

the NPRM (76 FR 62673, October 11, 

2011) as paragraphs (g)(3), (q)(1), and 

(q)(2) of this AD, respectively. 

• Redesignated paragraph (n) of the 

NPRM (76 FR 62673, October 11, 2011) 

as paragraph (q)(3) of this AD, and 

redesignated subsequent paragraphs 

accordingly. 

• We have revised paragraphs (g), (i), 

(o)(1), (o)(3), (o)(4), and (o)(5) of this AD 

to clarify the specific actions for which 

the specified service information is 

required. 

• We have revised the headings of 

Tables 1, 2, 3, 4, 5, and 6 of this AD to 

clarify the purpose of the content in 

those tables. 

• We have revised the wording in 

paragraphs (q)(1), (q)(2), (q)(3), and 

(q)(4) of this AD (Notes 2 and 3 and 

paragraphs (n) and (r) of the NPRM (76 

FR 62673, October 11, 2011), 

respectively); this change has not 

changed the intent of these paragraphs. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

62673, October 11, 2011) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 62673, 

October 11, 2011). 

Costs of Compliance 

We estimate that this AD will affect 

about 155 products of U.S. registry. 

The actions that are required by AD 

2010–23–26, Amendment 39–16516 (75 

FR 74610, December 1, 2010), and 

retained in this AD take about 79 workhours per product, at an average labor 

rate of $85 per work hour. Required 

parts cost about $10,270 per product. 

Based on these figures, the estimated 

cost of the currently required actions is 

$16,985 per product. 

We estimate that it will take about 100 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Based on these figures, we 

estimate the cost of the AD on U.S. 

operators to be $1,317,500, or $8,500 per 

product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM (76 FR 62673, 

October 11, 2011), the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Amendment 39–16516 (75 FR 

74610, December 1, 2010) and adding 

the following new AD: 

2012–01–05 Airbus: Amendment 39–16917. 

Docket No. FAA–2011–1066; Directorate 

Identifier 2011–NM–050–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective June 12, 2012. 

(b) Affected ADs 

This AD supersedes AD 2010–23–26, 

Amendment 39–16516 (75 FR 74610, 

December 1, 2010). 

(c) Applicability 

This AD applies to the airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD; except 

airplanes on which Airbus Modification 

11912 or 11932 has been installed. 

(1) Airbus Model A300 B2–1C, B2K–3C, 

B2–203, B4–2C, B4–103, and B4–203 

airplanes. 

(2) Airbus Model A300 B4–601, B4–603, 

B4–620, B4–622, B4–605R, B4–622R, and 

F4–605R airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57: Wings. 

(e) Reason 

This AD was prompted by new cases of 

cracks discovered during scheduled 

maintenance checks. We are issuing this AD 

to prevent cracking of the Gear Rib 5 righthand and left-hand attachment fitting at the 

lower flanges of the main landing gear 

(MLG), which could result in failed bolts 

penetrating through the rear spar and into a 

fuel tank, consequent fuel loss, and reduced 

structural integrity of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

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Federal Register / Vol. 77, No. 89 / Tuesday, May 8, 2012 / Rules and Regulations 26939 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Repetitive Inspections 

This paragraph restates the requirements of 

paragraph (g) of AD 2010–23–26, 

Amendment 39–16516 (75 FR 74610, 

December 1, 2010). Perform a detailed 

inspection and a high-frequency eddy current 

(HFEC) inspection to detect cracks in Gear 

Rib 5 of the MLG attachment fittings at the 

lower flange, in accordance with the 

Accomplishment Instructions of any 

applicable service bulletin listed in table 1 

and table 2 of this AD, at the time specified 

in paragraph (g)(1) or (g)(2) of this AD. After 

April 12, 2000 (the effective date of AD 

2000–05–07, Amendment 39–11616 (65 FR 

12077, March 8, 2000)), the service bulletins 

listed in table 2 of this AD must be used to 

accomplish the actions required by this 

paragraph. Repeat the inspections thereafter 

at intervals not to exceed 1,500 flight cycles, 

until the actions specified in paragraph (i), 

(j), or (l) of this AD are accomplished. 

TABLE 1—REVISION 01 OF SERVICE BULLETINS FOR PARAGRAPH (g) OF THIS AD 

Model— Airbus Service Bulletin— Revision— Dated— 

A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R and 

F4-605R airplanes.

A300-57-6087 ................................. 01 March 11, 1998. 

A300 B2-1C, B2K–3C, B2-203, B4-2C, B4-103, and B4-203 airplanes A300–57–0234 ............................... 01 March 11, 1998. 

TABLE 2—OTHER REVISIONS OF SERVICE BULLETINS FOR PARAGRAPH (g) OF THIS AD 

Model— Airbus Service Bulletin— Revision— Dated— 

A300 B4-601, B4-603, B4-620, B4-622, B4-605R, 

B4-622R, and F4-605R airplanes.

A300-57A6087 ...................... 02, including Appendix 01 .... June 24, 1999. 

03, including Appendix 01 .... May 19, 2000. 

04, including Appendix 01 .... February 19, 2002. 

05, including Appendix 01 .... March 10, 2008. 

A300 B2-1C, B2K–3C, B2-203, B4-2C, B4-103, and 

B4-203 airplanes.

A300-57A0234 ...................... 02 June 24, 1999. 

03, including Appendix 01 .... September 2, 1999. 

04, including Appendix 01 .... May 19, 2000. 

05, including Appendix 01 .... February 19, 2002. 

(1) For airplanes that have accumulated 

20,000 or more total flight cycles as of March 

9, 1998 (the effective date of AD 98–03–06, 

Amendment 39–10298 (63 FR 5224, February 

2, 1998)): Inspect within 500 flight cycles 

after March 9, 1998. 

(2) For airplanes that have accumulated 

less than 20,000 total flight cycles as of 

March 9, 1998 (the effective date of AD 98– 

03–06, Amendment 39–10298 (63 FR 5224, 

February 2, 1998)): Inspect prior to the 

accumulation of 18,000 total flight cycles, or 

within 1,500 flight cycles after March 9, 

1998, whichever occurs later. 

(3) For the purposes of this AD, a detailed 

inspection is defined as: ‘‘An intensive visual 

examination of a specific structural area, 

system, installation, or assembly to detect 

damage, failure, or irregularity. Available 

lighting is normally supplemented with a 

direct source of good lighting at intensity 

deemed appropriate by the inspector. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be used. Surface cleaning 

and elaborate access procedures may be 

required.’’ 

(h) Retained Repair for Any Crack Found 

During Inspections Required by Paragraph 

(g) of This AD 

This paragraph restates the requirements of 

paragraph (h) of AD 2010–23–26, 

Amendment 39–16516 (75 FR 74610, 

December 1, 2010). If any crack is detected 

during any inspection required by paragraph 

(g) of this AD, prior to further flight, 

accomplish the requirements of paragraph 

(h)(1) or (h)(2) of this AD, as applicable. 

(1) If a crack is detected at one hole only, 

and the crack does not extend out of the 

spotface of the hole, repair in accordance 

with the Accomplishment Instructions of the 

applicable service bulletin in table 2 of this 

AD. 

(2) If a crack is detected at more than one 

hole, or if any crack at any hole extends out 

of the spotface of the hole, repair in 

accordance with a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 

(i) Retained Terminating Modification for 

Repetitive Inspections Required by 

Paragraphs (g) and (j) of This AD 

This paragraph restates the requirements of 

paragraph (i) of AD 2010–23–26, Amendment 

39–16516 (75 FR 74610, December 1, 2010). 

Except as required by paragraph (l) of this 

AD, prior to the accumulation of 21,000 total 

flight cycles, or within 2 years after October 

20, 1999 (the effective date of AD 99–19–26, 

Amendment 39–11313 (64 FR 49966, 

September 15, 1999)), whichever occurs later: 

Modify Gear Rib 5 of the MLG attachment 

fittings at the lower flange in accordance 

with the Accomplishment Instructions of the 

applicable service bulletin in table 3 of this 

AD. After July 18, 2006 (the effective date of 

AD 2006–12–13, Amendment 39–14639 (71 

FR 33994, June 13, 2006)), Airbus Service 

Bulletin A300–57–6088, Revision 04, dated 

December 3, 2003 (for Model A300 B4–601, 

B4–603, B4–620, B4–622, B4–605R, B4– 

622R, and F4–605R airplanes); and Airbus 

Service Bulletin A300–57–0235, Revision 04, 

dated March 13, 2003, or Revision 05, dated 

December 3, 2003 (for Model A300 B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes); must be used to accomplish 

the actions required by this paragraph. 

Accomplishment of this modification 

constitutes terminating action for the 

repetitive inspection requirements of 

paragraphs (g) and (j) of this AD. 

TABLE 3—SERVICE BULLETINS FOR TERMINATING MODIFICATION REQUIRED BY PARAGRAPH (i) OF THIS AD 

Model— Airbus Service Bulletin— Revision— Dated— 

A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4– 

622R, and F4–605R airplanes.

A300–57–6088 ..................... 01, including Appendix 01 .... February 1, 1999. 

02 September 5, 2002. 

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26940 Federal Register / Vol. 77, No. 89 / Tuesday, May 8, 2012 / Rules and Regulations 

TABLE 3—SERVICE BULLETINS FOR TERMINATING MODIFICATION REQUIRED BY PARAGRAPH (i) OF THIS AD—Continued 

Model— Airbus Service Bulletin— Revision— Dated— 

04 December 3, 2003. 

A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes.

A300–57–0235 ..................... 01, including Appendix 01 .... February 1, 1999. 

03 September 5, 2002. 

04 March 13, 2003. 

05 December 3, 2003. 

(j) Retained Additional Repetitive 

Inspections 

This paragraph restates the requirements of 

paragraph (j) of AD 2010–23–26, Amendment 

39–16516 (75 FR 74610, December 1, 2010). 

For airplanes on which the modification 

specified in paragraph (i) or (l) of this AD has 

not been done before July 18, 2006 (the 

effective date of AD 2006–12–13, 

Amendment 39–14639 (71 FR 33994, June 

13, 2006)), perform a detailed and an HFEC 

inspection to detect cracks of the lower 

flange of Gear Rib 5 of the MLG at holes 43, 

47, 48, 49, 50, 52, and 54, in accordance with 

the applicable service bulletin listed in table 

4 of this AD. Perform the inspections at the 

applicable time specified in paragraph (j)(1), 

(j)(2), (j)(3), or (j)(4) of this AD. Repeat the 

inspections thereafter at intervals not to 

exceed 700 flight cycles until the terminating 

modification required by paragraph (l) of this 

AD is accomplished. Accomplishment of the 

inspections per paragraph (j) of this AD 

terminates the inspection requirements of 

paragraph (g) of this AD. 

TABLE 4—SERVICE BULLETINS FOR REPETITIVE INSPECTIONS REQUIRED BY PARAGRAPH (j) OF THIS AD 

Model— Airbus Service Bulletin— Revision— Dated— 

A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4– 

622R, and F4–605R airplanes.

A300–57A6087 ..................... 04, including Appendix 01 .... February 19, 2002. 

05, including Appendix 01 March 10, 2008. 

A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes.

A300–57A0234 ..................... 05, including Appendix 01 .... February 19, 2002. 

(1) For Model A300 B2–1C, B2K–3C, B2– 

203, B4–2C, B4–103, and B4–203 airplanes; 

and Model A300 B4–601, B4–603, B4–620, 

B4–622, B4–605R, B4–622R, and F4–605R 

airplanes that have accumulated 18,000 or 

more total flight cycles as of July 18, 2006 

(the effective date of AD 2006–12–13, 

Amendment 39–14639 (71 FR 33994, June 

13, 2006)): Within 700 flight cycles after July 

18, 2006. 

(2) For Model A300 B2–1C, B2K–3C, and 

B2–203 airplanes that have accumulated less 

than 18,000 total flight cycles as of July 18, 

2006 (the effective date of AD 2006–12–13, 

Amendment 39–14639 (71 FR 33994, June 

13, 2006)): Prior to the accumulation of 

18,000 total flight cycles, or within 700 flight 

cycles after July 18, 2006, whichever occurs 

later. 

(3) For Model A300 B4–2C, B4–103, and 

B4–203 airplanes that have accumulated less 

than 18,000 total flight cycles as of July 18, 

2006 (the effective date of AD 2006–12–13, 

Amendment 39–14639 (71 FR 33994, June 

13, 2006)): Prior to the accumulation of 

14,500 total flight cycles, or within 700 flight 

cycles after July 18, 2006, whichever occurs 

later. 

(4) For Model A300 B4–601, B4–603, B4– 

620, B4–622, B4–605R, B4–622R, and F4– 

605R airplanes that have accumulated less 

than 18,000 total flight cycles as of July 18, 

2006 (the effective date of AD 2006–12–13, 

Amendment 39–14639 (71 FR 33994, June 

13, 2006)): Prior to the accumulation of 

11,600 total flight cycles, or within 700 flight 

cycles after July 18, 2006, whichever occurs 

later. 

(k) Retained Crack Repair 

This paragraph restates the requirements of 

paragraph (k) of AD 2010–23–26, 

Amendment 39–16516 (75 FR 74610, 

December 1, 2010). If any crack is detected 

during any inspection required by paragraph 

(j) of this AD, prior to further flight, 

accomplish the requirements of paragraphs 

(k)(1) and (k)(2) of this AD, as applicable. 

(1) If a crack is detected at only one hole, 

and the crack does not extend out of the 

spotface of the hole, repair in accordance 

with Airbus Service Bulletin A300–57A0234, 

Revision 05, including Appendix 01, dated 

February 19, 2002 (for Model A300 B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes); or A300–57A6087, Revision 

04, including Appendix 01, dated February 

19, 2002, or A300–57A6087, Revision 05, 

including Appendix 01, dated March 10, 

2008 (for Model A300 B4–601, B4–603, B4– 

620, B4–622, B4–605R, B4–622R, and F4– 

605R airplanes). 

(2) If a crack is detected at more than one 

hole, or if any crack at any hole extends out 

of the spotface of the hole, repair in 

accordance with a method approved by the 

Manager, International Branch, ANM–116, or 

the EASA (or its delegated agent). 

(l) Retained Terminating Modification for 

Repetitive Inspections Required by 

Paragraphs (g) and (j) of This AD for Certain 

Airplanes 

This paragraph restates the requirements of 

paragraph (l) of AD 2010–23–26, Amendment 

39–16516 (75 FR 74610, December 1, 2010). 

For airplanes on which the terminating 

modification in paragraph (i) of this AD has 

not been accomplished before July 18, 2006 

(the effective date of AD 2006–12–13, 

Amendment 39–14639 (71 FR 33994, June 

13, 2006)): At the earlier of the times 

specified in paragraphs (l)(1) and (l)(2) of this 

AD, modify Gear Rib 5 of the MLG 

attachment fittings at the lower flange. 

Except as provided by paragraph (m) of this 

AD, do the modification in accordance with 

the applicable service bulletin identified in 

table 5 of this AD. This action terminates the 

repetitive inspections requirements of 

paragraphs (g) and (j) of this AD. 

(1) Prior to the accumulation of 21,000 

total flight cycles, or within 2 years after 

October 20, 1999 (the effective date of AD 

99–19–26, Amendment 39–11313 (64 FR 

49966, September 15, 1999)), whichever is 

later. 

(2) Within 16 months after July 18, 2006 

(the effective date of AD 2006–12–13, 

Amendment 39–14639 (71 FR 33994, June 

13, 2006)). 

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Federal Register / Vol. 77, No. 89 / Tuesday, May 8, 2012 / Rules and Regulations 26941 

TABLE 5—SERVICE BULLETINS FOR TERMINATING MODIFICATION REQUIRED BY PARAGRAPH (l) OF THIS AD 

Model— Airbus Service Bulletin— Revision— Dated— 

A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R and F4– 

605R airplanes.

A300–57–6088 ............................... 04 December 3, 

2003. 

A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes.A300–57–0235 ............................... 04 March 13, 2003. 

05 December 3, 

2003. 

(m) Retained Modification 

This paragraph restates the requirements of 

paragraph (m) of AD 2010–23–26, 

Amendment 39–16516 (75 FR 74610, 

December 1, 2010). Where the applicable 

service bulletin specified in paragraph (l) of 

this AD specifies to contact Airbus for 

modification instructions; or if there is a 

previously installed repair at any of the 

affected fastener holes; or if a crack is found 

when accomplishing the modification: Prior 

to further flight, modify in accordance with 

a method approved by the Manager, 

International Branch, ANM–116, or the 

EASA (or its delegated agent). 

(n) Retained Exception for No Reporting 

This paragraph restates the requirements of 

paragraph (o) of AD 2010–23–26, 

Amendment 39–16516 (75 FR 74610, 

December 1, 2010). Although the service 

bulletins identified in tables 1, 2, 3, 4, 5, and 

6 of this AD specify to submit certain 

information to the manufacturer, this AD 

does not include such a requirement. 

(o) Retained Requirements With Revised 

Service Information 

This paragraph restates the requirements of 

paragraph (p) of AD 2010–23–26, 

Amendment 39–16516 (75 FR 74610, 

December 1, 2010). Unless already done, do 

the following actions. 

(1) At the applicable time specified in 

paragraph (o)(2) of this AD, perform a 

detailed inspection for cracking at the 

locations specified in paragraphs (o)(1)(i), 

(o)(1)(ii), and (o)(1)(iii) of this AD, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–57A0246, Revision 03, 

including Appendices 1 and 2, dated March 

11, 2009, or Revision 04, including 

Appendices 1 and 2, dated September 9, 

2009 (for Model A300 B2–1C, B2K–3C, B2– 

203, B4–2C, B4–103, and B4–203 airplanes); 

or Airbus Mandatory Service Bulletin A300– 

57A6101, Revision 03, including Appendices 

1 and 2, dated March 11, 2009, or Revision 

04, including Appendices 1 and 2, dated 

September 9, 2009 (for Model A300 B4–601, 

B4–603, B4–620, B4–622, B4–605R, B4–622R 

and F4–605R airplanes). As of the effective 

date of this AD Revision 04 of these service 

bulletins must be used to accomplish the 

actions required by this paragraph. 

(i) The bottom flange and vertical web in 

the area between the wing rear spar/gear Rib 

5 attachment and the forward reaction-rod 

pick-up lug. 

(ii) On the inboard side, around the 

fastener holes at locations 43, 47 to 50, 52, 

and 54. 

(iii) On the outboard side, the lower flange, 

the vertical web and around the fastener 

holes at locations 43, 47 to 50, 52 and 54. 

(2) Do the inspection required by 

paragraph (o)(1) of this AD at the later of the 

times in paragraphs (o)(2)(i) and (o)(2)(ii) of 

this AD. 

(i) Within 400 flight cycles after the 

accomplishment of the actions required by 

paragraph (i) or (l) of this AD, as applicable. 

(ii) Within 400 flight cycles or 4 months 

after January 5, 2011 (the effective date of AD 

2010–23–26, Amendment 39–16516 (75 FR 

74610, December 1, 2010)), whichever occurs 

first. 

(3) If no cracking is detected during the 

inspection required by paragraph (o)(1) of 

this AD, before further flight, perform a 

fluorescent penetrant inspection (FPI) at 

holes location 47 and 54, in the right-hand 

and left-hand MLG Rib 5 attachment fitting 

lower flange, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–57A0246, 

Revision 03, including Appendices 1 and 2, 

dated March 11, 2009, or Revision 04, 

including Appendices 1 and 2, dated 

September 9, 2009 (for Model A300 B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes); or Airbus Mandatory Service 

Bulletin A300–57A6101, Revision 03, 

including Appendices 1 and 2, dated March 

11, 2009, or Revision 04, including 

Appendices 1 and 2, dated September 9, 

2009 (for Model A300 B4–601, B4–603, B4– 

620, B4–622, B4–605R, B4–622R and F4– 

605R airplanes). As of the effective date of 

this AD, Airbus Mandatory Service Bulletin 

A300–57A0246, Revision 04, including 

Appendices 1 and 2, dated September 9, 

2009; or Airbus Mandatory Service Bulletin 

A300–57A6101, Revision 04, including 

Appendices 1 and 2, dated September 9, 

2009; as applicable; must be used to 

accomplish the actions required by this 

paragraph. 

(4) Thereafter, at intervals not to exceed 

400 flight cycles, repeat the detailed and FPI 

inspections, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–57A0246, 

Revision 03, including Appendices 1 and 2, 

dated March 11, 2009, or Revision 04, 

including Appendices 1 and 2, dated 

September 9, 2009 (for Model A300 B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes); or Airbus Mandatory Service 

Bulletin A300–57A6101, Revision 03, 

including Appendices 1 and 2, dated March 

11, 2009, or Revision 04, including 

Appendices 1 and 2, dated September 9, 

2009 (for Model A300 B4–601, B4–603, B4– 

620, B4–622, B4–605R, B4–622R and F4– 

605R airplanes); until the terminating action 

required by paragraph (p) of this AD has been 

accomplished. As of the effective date of this 

AD, Airbus Mandatory Service Bulletin 

A300–57A0246, Revision 04, including 

Appendices 1 and 2, dated September 9, 

2009; or Airbus Mandatory Service Bulletin 

A300–57A6101, Revision 04, including 

Appendices 1 and 2, dated September 9, 

2009; as applicable; must be used to 

accomplish the actions required by this 

paragraph. 

(5) If any crack is detected during any of 

the inspections required by paragraphs (o)(1), 

(o)(3), and (o)(4) of this AD, and Airbus 

Mandatory Service Bulletin A300–57A0246, 

Revision 03, including Appendices 1 and 2, 

dated March 11, 2009, or Revision 04, 

including Appendices 1 and 2, dated 

September 9, 2009 (for Model A300 B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes); or Airbus Mandatory Service 

Bulletin A300–57A6101, Revision 03, 

including Appendices 1 and 2, dated March 

11, 2009, or Revision 04, including 

Appendices 1 and 2, dated September 9, 

2009 (for Model A300 B4–601, B4–603, B4– 

620, B4–622, B4–605R, B4–622R and F4– 

605R airplanes); recommends contacting 

Airbus for appropriate action: Before further 

flight, contact Airbus for a repair solution, 

and do the repair; or repair the cracking 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, or EASA (or its 

delegated agent). 

(p) New Terminating Action 

Within 30 months after the effective date 

of this AD: Modify the spot-faces around all 

the fastener holes at locations 43, 47 to 50, 

52, and 54 (except for spot-faces of holes 

which have been previously repaired) on the 

bottom flange MLG ribs, in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–57–0254, 

Revision 01, including Appendix 1, dated 

June 14, 2011 (for Model A300 B2–1C, B2K– 

3C, B2–203, B4–2C, B4–103, and B4–203 

airplanes); or Airbus Mandatory Service 

Bulletin A300–57–6110, Revision 01, 

including Appendix 1, dated June 6, 2011 

A300 B4–601, B4–603, B4–620, B4–622, B4– 

605R, B4–622R and F4–605R airplanes (for 

Model A300 B4–601, B4–603, B4–620, B4– 

622, B4–605R, B4–622R and F4–605R 

airplanes). Accomplishing this modification 

terminates the repetitive inspection 

requirements of paragraph (o)(4) of this AD. 

(q) Credit for Previous Actions 

(1) This paragraph provides credit for 

initial detailed and HFEC inspections, as 

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26942 Federal Register / Vol. 77, No. 89 / Tuesday, May 8, 2012 / Rules and Regulations 

required by the introductory text of 

paragraph (g) of this AD, if those inspections 

were performed before April 12, 2000 (the 

effective date of AD 2000–05–07, 

Amendment 39–11616 (65 FR 12077, March 

8, 2000)), using Airbus Service Bulletin 

A300–57A0234 (for Model A300 B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes) or A300–57A6087, both dated 

August 5, 1997 (for Model A300 B4–601, B4– 

603, B4–620, B4–622, B4–605R, B4–622R, 

and F4–605R airplanes). 

(2) This paragraph provides credit for a 

modification, as required by paragraph (i) of 

this AD, if the modification was performed 

before April 12, 2000 (the effective date of 

AD 2000–05–07, Amendment 39–11616 (65 

FR 12077, March 8, 2000)), using Airbus 

Service Bulletin A300–57–6088, dated 

August 5, 1998 (for Model A300 B4–601, B4– 

603, B4–620, B4–622, B4–605R, B4–622R and 

F4–605R airplanes); or Airbus Service 

Bulletin A300–57–0235, dated August 5, 

1998 (for Model A300 B2–1C, B2K–3C, B2– 

203, B4–2C, B4–103, and B4–203 airplanes). 

(3) This paragraph provides credit for the 

actions required by paragraphs (i) and (l) of 

this AD, if those actions were performed 

before July 18, 2006 (the effective date of AD 

2006–12–13, Amendment 39–14639 (71 FR 

33994, June 13, 2006)), using the applicable 

service information listed in table 6 of this 

AD. 

TABLE 6—PREVIOUS ISSUES OF CERTAIN SERVICE BULLETINS

Model— Airbus Service Bulletin— Revision— Dated— 

A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes.

A300–57–0235 ..................... 02, including Appendix 01 .... September 27, 

1999. 

03 September 5, 2002. 

A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4– 

622R and F4–605R airplanes.

A300–57–6088 ..................... 02 .......................................... September 5, 2000. 

03 .......................................... March 13, 2003. 

(4) This paragraph provides credit for a 

modification of the spot-faces, as specified in 

paragraph (p) of this AD, if the modification 

was performed before the effective date of 

this AD using Airbus Mandatory Service 

Bulletin A300–57–0254, dated June 4, 2010 

(for Model A300 B2–1C, B2K–3C, B2–203, 

B4–2C, B4–103, and B4–203 airplanes); or 

Airbus Mandatory Service Bulletin A300–57– 

6110, dated June 7, 2010 (for Model A300 

B4–601, B4–603, B4–620, B4–622, B4–605R, 

B4–622R and F4–605R airplanes). 

(r) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–2125; fax (425) 

227–1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. AMOCs approved previously in 

accordance with AD 2000–05–07, 

Amendment 39–11616 (65 FR 12077, March 

8, 2000); AD 2006–12–13, Amendment 39– 

14639 (71 FR 33994, June 13, 2006); and AD 

2010–23–26, Amendment 39–16516 (75 FR 

74610, December 1, 2010); are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(s) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0029, dated February 24, 

2011, and the service information specified 

in paragraphs (s)(1) through (s)(23) of this 

AD, for related information. 

(1) Airbus Service Bulletin A300–57–0234, 

Revision 01, dated March 11, 1998. 

(2) Airbus Service Bulletin A300–57A0234, 

Revision 02, dated June 24, 1999. 

(3) Airbus Service Bulletin A300–57A0234, 

Revision 03, including Appendix 01, dated 

September 2, 1999. 

(4) Airbus Service Bulletin A300–57A0234, 

Revision 04, including Appendix 01, dated 

May 19, 2000. 

(5) Airbus Service Bulletin A300–57A0234, 

Revision 05, including Appendix 01, dated 

February 19, 2002. 

(6) Airbus Service Bulletin A300–57–0235, 

Revision 01, including Appendix 01, dated 

February 1, 1999. 

(7) Airbus Service Bulletin A300–57–0235, 

Revision 03, dated September 5, 2002. 

(8) Airbus Service Bulletin A300–57–0235, 

Revision 04, dated March 13, 2003. 

(9) Airbus Service Bulletin A300–57–0235, 

Revision 05, dated December 3, 2003. 

(10) Airbus Mandatory Service Bulletin 

A300–57A0246, Revision 03, including 

Appendices 1 and 2, dated March 11, 2009. 

(11) Airbus Mandatory Service Bulletin 

A300–57A0246, Revision 04, including 

Appendices 1 and 2, dated September 9, 

2009. 

(12) Airbus Mandatory Service Bulletin 

A300–57–0254, Revision 01, including 

Appendix 1, dated June 14, 2011. 

(13) Airbus Service Bulletin A300–57– 

6087, Revision 01, dated March 11, 1998. 

(14) Airbus Service Bulletin A300– 

57A6087, Revision 02, including Appendix 

01, dated June 24, 1999. 

(15) Airbus Service Bulletin A300– 

57A6087, Revision 03, including Appendix 

01, dated May 19, 2000. 

(16) Airbus Service Bulletin A300– 

57A6087, Revision 04, including Appendix 

01, dated February 19, 2002. 

(17) Airbus Service Bulletin A300– 

57A6087, Revision 05, including Appendix 

01, dated March 10, 2008. 

(18) Airbus Service Bulletin A300–57– 

6088, Revision 01, including Appendix 01, 

dated February 1, 1999. 

(19) Airbus Service Bulletin A300–57– 

6088, Revision 02, dated September 5, 2002. 

(20) Airbus Service Bulletin A300–57– 

6088, Revision 04, dated December 3, 2003. 

(21) Airbus Mandatory Service Bulletin 

A300–57A6101, Revision 03, including 

Appendices 1 and 2, dated March 11, 2009. 

(22) Airbus Mandatory Service Bulletin 

A300–57A6101, Revision 04, including 

Appendices 1 and 2, dated September 9, 

2009. 

(23) Airbus Mandatory Service Bulletin 

A300–57–6110, Revision 01, including 

Appendix 1, dated June 6, 2011. 

(t) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51 on the date 

specified. 

(2) The following service information was 

approved for IBR on June 12, 2012: 

(i) Airbus Mandatory Service Bulletin 

A300–57–0254, Revision 01, including 

Appendix 1, dated June 14, 2011. 

(ii) Airbus Mandatory Service Bulletin 

A300–57–6110, Revision 01, including 

Appendix 1, dated June 6, 2011. 

(3) The following service information was 

approved for IBR January 5, 2011 (75 FR 

74610, December 1, 2010): 

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Federal Register / Vol. 77, No. 89 / Tuesday, May 8, 2012 / Rules and Regulations 26943 

(i) Airbus Mandatory Service Bulletin 

A300–57A0246, Revision 03, including 

Appendices 1 and 2, dated March 11, 2009. 

(ii) Airbus Mandatory Service Bulletin 

A300–57A0246, Revision 04, including 

Appendices 1 and 2, dated September 9, 

2009. 

(iii) Airbus Mandatory Service Bulletin 

A300–57A6101, Revision 03, including 

Appendices 1 and 2, dated March 11, 2009. 

(iv) Airbus Mandatory Service Bulletin 

A300–57A6101, Revision 04, including 

Appendices 1 and 2, dated September 9, 

2009. 

(v) Airbus Service Bulletin A300–57A6087, 

Revision 05, including Appendix 01, dated 

March 10, 2008. (Appendix 01 of this 

document was incorrectly identified as 

‘‘Appendix 05’’ in the document citation 

specified in table 8 of AD 2010–23–26, 

Amendment 39–16516 (75 FR 74610, 

December 1, 2010); all other references to 

Appendix 01 of this document in AD 2010– 

23–26 were correct.) 

(4) The following service information was 

approved for IBR July 18, 2006 (71 FR 33994, 

June 13, 2006): 

(i) Airbus Service Bulletin A300–57A0234, 

Revision 04, including Appendix 01, dated 

May 19, 2000. 

(ii) Airbus Service Bulletin A300– 

57A0234, Revision 05, including Appendix 

01, dated February 19, 2002. 

(iii) Airbus Service Bulletin A300– 

57A6087, Revision 03, including Appendix 

01, dated May 19, 2000. 

(iv) Airbus Service Bulletin A300– 

57A6087, Revision 04, including Appendix 

01, dated February 19, 2002. 

(v) Airbus Service Bulletin A300–57–0235, 

Revision 03, dated September 5, 2002. 

(vi) Airbus Service Bulletin A300–57– 

0235, Revision 04, dated March 13, 2003. 

(vii) Airbus Service Bulletin A300–57– 

0235, Revision 05, dated December 3, 2003. 

(viii) Airbus Service Bulletin A300–57– 

6088, Revision 02, dated September 5, 2002. 

(ix) Airbus Service Bulletin A300–57– 

6088, Revision 04, dated December 3, 2003. 

(5) The following service information was 

approved for IBR on April 12, 2000 (65 FR 

12077, March 8, 2000): 

(i) Airbus Service Bulletin A300–57A0234, 

Revision 02, dated June 24, 1999. 

(ii) Airbus Service Bulletin A300– 

57A0234, Revision 03, including Appendix 

01, dated September 2, 1999. 

(iii) Airbus Service Bulletin A300– 

57A6087, Revision 02, including Appendix 

01, dated June 24, 1999. 

(6) The following service information was 

approved for IBR on October 20, 1999 (64 FR 

49966, September 15, 1999). 

(i) Airbus Service Bulletin A300–57–0234, 

Revision 01, dated March 11, 1998. 

(ii) Airbus Service Bulletin A300–57–0235, 

Revision 01, including Appendix 01, dated 

February 1, 1999. 

(iii) Airbus Service Bulletin A300–57– 

6087, Revision 01, dated March 11, 1998. 

(iv) Airbus Service Bulletin A300–57– 

6088, Revision 01, including Appendix 01, 

dated February 1, 1999. 

(7) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(8) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(9) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on January 

6, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–9189 Filed 5–7–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0417; Directorate 

Identifier 2012–NE–11–AD; Amendment 39– 

17045; AD 2012–09–10] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada Turboprop Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Pratt & Whitney Canada PT6A–38, –41, 

–42, –42A, –61, –64, –66, –66B, –110, 

–112, –114, –114A, –121, –135, and 

–135A series turboprop engines. This 

AD requires removal from service of 

certain part manufacturer approval 

(PMA) replacement Timken Alcor 

Aerospace Technologies, Inc. (TAATI) 

first stage sun gears and planet gears 

installed in the reduction gearbox. This 

AD was prompted by failures of certain 

first stage sun gears manufactured by 

TAATI. We are issuing this AD to 

prevent failure of the sun gear and 

planet gears which will result in an 

engine in-flight shut down, possible 

uncontained engine failure, aircraft 

damage, and serious injuries. 

DATES: This AD becomes effective May 

23, 2012. 

We must receive comments on this 

AD by June 22, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: 202–493–2251. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (phone: 

800–647–5527) is the same as the Mail 

address provided in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Paul 

Craig, Aerospace Engineer, Los Angeles 

Aircraft Certification Office, FAA, 3960 

Paramount Blvd., Suite 100, Lakewood, 

CA 90712; phone: 562–627–5252; fax: 

562–627–5210; email: 

paul.craig@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received two reports of sun gears, 

part number (P/N) E3028456, and 

installed in reduction gearboxes, failing 

during operation. We also received one 

report of a sun gear, P/N E3037304, 

showing premature wear and broken 

gear teeth during inspection. All three 

gear failures occurred between 60 and 

127 hours of operation time-since-new. 

These conditions, if not corrected, could 

result in failure of the sun gear and 

planet gears in the propeller reduction 

gearbox assembly, which will result in 

an engine in-flight shut down, possible 

uncontained engine failure, aircraft 

damage, and serious injuries. We 

determined that the affected PMA 

replacement TAATI first stage sun gears 

and planet gears listed in this AD, 

would have been installed after 

December 22, 2008. The affected parts 

are listed as follows: 

First stage sun gears P/N E3028456, 

all serial numbers (S/Ns), and the 

associated planet gears. 

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