1990 Federal Register / Vol. 76, No. 8 / Wednesday, January 12, 2011 / Rules and Regulations 

TABLE 6—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE

Document Date Manual 

Shorts Advance Amendment Bulletin 1/2004 .... July 13, 2004 .................................................... Shorts Airplane Flight Manuals (AFMs) 

SBH.3.2, SBH.3.3, SBH.3.6, SBH.3.7, 

SBH.3.8, and SB.3.9. 

Shorts Advance Amendment Bulletin 1/2004 .... July 13, 2004 .................................................... Shorts AFMs SB.4.3, SB.4.6, and SB.4.8. 

Shorts Advance Amendment Bulletin 1/2004 .... July 13, 2004 .................................................... Shorts AFM SB.5.2.

Shorts Advance Amendment Bulletin 1/2004 .... July 13, 2004 .................................................... Shorts AFM SB.6.2.

Shorts Temporary Revision TR330–AMM–13 ... June 21, 2004 .................................................. SD3–30 AMM. 

Shorts Temporary Revision TR330–AMM–14 ... June 21, 2004 .................................................. SD3–30 AMM. 

Shorts Temporary Revision TR360–AMM–33 ... July 27, 2004 .................................................... SD3–60 AMM. 

Shorts Temporary Revision TR360–AMM–34 ... July 27, 2004 .................................................... SD3–60 AMM. 

Shorts Temporary Revision TRSD360S–AMM– 

14.

July 29, 2004 .................................................... SD3–60 SHERPA AMM. 

Shorts Temporary Revision TRSD360S–AMM– 

15.

July 29, 2004 .................................................... SD3–60 SHERPA AMM. 

Shorts Temporary Revision TRSD3S–AMM–15 July 28, 2004 .................................................... SD3 SHERPA AMM. 

Shorts Temporary Revision TRSD3S–AMM–16 July 28, 2004 .................................................... SD3 SHERPA AMM. 

Shorts Service Bulletin SD330–28–37 .............. June 2004 ........................................................ None. 

Shorts Service Bulletin SD360–28–23 .............. June 2004 ........................................................ None. 

Shorts Service Bulletin SD360 SHERPA–28–3 June 2004 ........................................................ None. 

Shorts Service Bulletin SD3 SHERPA–28–2 .... June 2004 ........................................................ None. 

(3) For service information identified in 

this AD, contact Short Brothers PLC, 

Airworthiness, P.O. Box 241, Airport Road, 

Belfast, BT3 9DZ Northern Ireland; telephone 

+44(0)2890–462469; fax +44(0)2890–468444; 

e-mail 

michael.mulholland@aero.bombardier.com; 

Internet http://www.bombardier.com. 

(4) 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. 

(5) 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 NARA, 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 

November 10, 2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–30 Filed 1–11–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0622; Directorate 

Identifier 2009–CE–034–AD; Amendment 

[39–16570; AD 2009–18–03 R1] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Models PC–6, PC–6–H1, 

PC–6–H2, PC–6/350, PC–6/350–H1, PC– 

6/350–H2, PC–6/A, PC–6/A–H1, PC–6/ 

A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/ 

B2–H2, PC–6/B2–H4, PC–6/C–H2, and 

PC–6/C1–H2 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are revising an existing 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Findings of corrosion, wear and cracks in 

the upper wing strut fittings on some PC–6 

aircraft have been reported in the past. It is 

possible that the spherical bearing of the 

wing strut fittings installed in the underwing 

can be loose in the fitting or cannot rotate 

because of corrosion. In this condition, the 

joint cannot function as designed and fatigue 

cracks may then develop. Undetected cracks, 

wear and/or corrosion in this area could 

cause failure of the upper attachment fitting, 

leading to failure of the wing structure and 

subsequent loss of control of the aircraft. 

To address this problem, FOCA published 

AD TM–L Nr. 80.627–6/Index 72–2 and HB– 

2006–400 and EASA published AD 2007– 

0114 to require specific inspections and to 

obtain a fleet status. Since the issuance of AD 

2007–0114, the reported data proved that it 

was necessary to establish and require 

repetitive inspections. 

EASA published Emergency AD 2007– 

0241–E to extend the applicability and to 

require repetitive eddy current and visual 

inspections of the upper wing strut fitting for 

evidence of cracks, wear and/or corrosion 

and examination of the spherical bearing and 

replacement of cracked fittings. Collected 

data received in response to Emergency AD 

2007–0241–E resulted in the issuance of 

EASA AD 2007–0241R1 that permitted 

extending the intervals for the repetitive 

eddy current and visual inspections from 100 

Flight Hours (FH) to 300 FH and from 150 

Flight Cycles (FC) to 450 FC, respectively. In 

addition, oversize bolts were introduced by 

Pilatus PC–6 Service Bulletin (SB) 57–005 R1 

and the fitting replacement procedure was 

adjusted accordingly. 

Based on fatigue test results, EASA AD 

2007–0241R2 was issued to extend the 

repetitive inspection interval to 1100 FH or 

12 calendar months, whichever occurs first, 

and to delete the related flight cycle intervals 

and the requirement for the ‘‘Mild Corrosion 

Severity Zone’’. In addition, some editorial 

changes have been made for reasons of 

standardization and readability. 

Revision 3 of this AD referred to the latest 

revision of the PC–6 Aircraft Maintenance 

Manual (AMM) Chapter 5 limitations which 

have included the same repetitive inspection 

intervals and procedures already mandated 

in the revision 2 of AD 2007–0241. Besides 

the inspections, in the latest revision of the 

PC–6 AMM, the replacement procedures for 

the fittings were included. 

Additionally, EASA AD 2007–0241R3 

introduced the possibility to replace the wing 

strut fitting with a new designed wing strut 

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Federal Register / Vol. 76, No. 8 / Wednesday, January 12, 2011 / Rules and Regulations 1991 

fitting. With this optional part replacement, 

in the repetitive inspection procedure the 

1100 FH interval is deleted so that only 

calendar defined intervals of inspections 

remained applicable. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

February 16, 2011. 

As of October 1, 2009 (74 FR 43636, 

August 27, 2009), the Director of the 

Federal Register approved the 

incorporation by reference of Pilatus 

Aircraft Ltd. Pilatus PC–6 Service 

Bulletin No. 57–005, REV No. 2, dated 

May 19, 2008; and Chapter 57–00–02 of 

Pilatus Aircraft Ltd. Pilatus PC–6 

Aircraft Maintenance Manual, dated 

November 30, 2008 (referenced as 

revision 9 in EASA AD No.: 2007– 

0241R3) listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

For service information identified in 

this AD, contact PILATUS AIRCRAFT 

LTD., Customer Service Manager, CH– 

6371 STANS, Switzerland; telephone: 

+41 (0) 41 619 65 01; fax: +41 (0) 41 619 

65 76; Internet: http://www.pilatusaircraft.com. You may review copies of 

the referenced service information at the 

FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call 816–329– 

4148. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090. 

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 7, 2010 (75 FR 

62005), and proposed to revise AD 

2009–18–03, Amendment 39–15999 (74 

FR 43636, August 27, 2009). 

Since we issued AD 2009–18–03, 

Pilatus has updated their maintenance 

programs with new requirements and 

limitations. Another AD action, AD 

2011–01–14, requires the incorporation 

of the updated maintenance 

requirements into the airworthiness 

limitations section of the instructions 

for continued airworthiness. Those 

updated maintenance requirements 

include the repetitive inspections for 

the wing strut fittings and the spherical 

bearings currently included in AD 

2009–18–03. 

The NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states that: 

Findings of corrosion, wear and cracks in 

the upper wing strut fittings on some PC–6 

aircraft have been reported in the past. It is 

possible that the spherical bearing of the 

wing strut fittings installed in the underwing 

can be loose in the fitting or cannot rotate 

because of corrosion. In this condition, the 

joint cannot function as designed and fatigue 

cracks may then develop. Undetected cracks, 

wear and/or corrosion in this area could 

cause failure of the upper attachment fitting, 

leading to failure of the wing structure and 

subsequent loss of control of the aircraft. 

To address this problem, FOCA published 

AD TM–L Nr. 80.627–6/Index 72–2 and HB– 

2006–400 and EASA published AD 2007– 

0114 to require specific inspections and to 

obtain a fleet status. Since the issuance of AD 

2007–0114, the reported data proved that it 

was necessary to establish and require 

repetitive inspections. 

EASA published Emergency AD 2007– 

0241–E to extend the applicability and to 

require repetitive eddy current and visual 

inspections of the upper wing strut fitting for 

evidence of cracks, wear and/or corrosion 

and examination of the spherical bearing and 

replacement of cracked fittings. Collected 

data received in response to Emergency AD 

2007–0241–E resulted in the issuance of 

EASA AD 2007–0241R1 that permitted 

extending the intervals for the repetitive 

eddy current and visual inspections from 100 

Flight Hours (FH) to 300 FH and from 150 

Flight Cycles (FC) to 450 FC, respectively. In 

addition, oversize bolts were introduced by 

Pilatus PC–6 Service Bulletin (SB) 57–005 R1 

and the fitting replacement procedure was 

adjusted accordingly. 

Based on fatigue test results, EASA AD 

2007–0241R2 was issued to extend the 

repetitive inspection interval to 1100 FH or 

12 calendar months, whichever occurs first, 

and to delete the related flight cycle intervals 

and the requirement for the ‘‘Mild Corrosion 

Severity Zone’’. In addition, some editorial 

changes have been made for reasons of 

standardization and readability. 

Revision 3 of this AD referred to the latest 

revision of the PC–6 Aircraft Maintenance 

Manual (AMM) Chapter 5 limitations which 

have included the same repetitive inspection 

intervals and procedures already mandated 

in the revision 2 of AD 2007–0241. Besides 

the inspections, in the latest revision of the 

PC–6 AMM, the replacement procedures for 

the fittings were included. 

Additionally, EASA AD 2007–0241R3 

introduced the possibility to replace the wing 

strut fitting with a new designed wing strut 

fitting. With this optional part replacement, 

in the repetitive inspection procedure the 

1100 FH interval is deleted so that only 

calendar defined intervals of inspections 

remained applicable. 

The aim of this new revision is to only 

mandate the initial inspection requirement 

and consequently to limit its applicability to 

aeroplanes which are not already in 

compliance with EASA AD 2007–0241R3. 

All aeroplanes which are in compliance with 

EASA AD 2007–0241R3 have to follow the 

repetitive inspection requirements as 

described in Pilatus PC–6 AMM Chapter 04– 

00–00, Document Number 01975, Revision 

12 and the Airworthiness Limitations (ALS) 

Document Number 02334 Revision 1 

mandated by EASA AD 2010–0176. 

Therefore the repetitive inspection 

requirements corresponding paragraphs have 

been deleted in this new EASA AD revision. 

The paragraph numbers of EASA AD 2007– 

0241R numbering has been maintained for 

referencing needs. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request for Clarification on 

Applicability 

Pilatus Aircraft commented that there 

is no consistency between FAA 

Directorate Identifier 2010–CE–047–AD 

and FAA Directorate Identifier 2009– 

CE–034–AD regarding the applicability 

of airplanes in regards to the 

manufacturer serial numbers (MSN) on 

the Fairchild PC–6 airplanes. 

The FAA agrees that the applicability 

of airplanes needs corrected. We will 

change the applicability to clarify that 

some specific MSNs can also be 

identified as Fairchild Republic 

Company PC–6 airplanes, Fairchild 

Industries PC–6 airplanes, Fairchild 

Heli Porter PC–6 airplanes, or FairchildHiller Corporation PC–6 airplanes. 

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. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

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1992 Federal Register / Vol. 76, No. 8 / Wednesday, January 12, 2011 / Rules and Regulations 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

50 products of U.S. registry. We also 

estimate that it will take about 7 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate 

the cost of this AD on U.S. operators to 

be $29,750, or $595 per product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 30 work-hours and require parts 

costing $5,000, for a cost of $7,550 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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 

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 Management Facility between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains the NPRM, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket 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 39–15999 (74 FR 

43636, August 27, 2009) and adding the 

following new AD: 

2009–18–03 R1 Pilatus Aircraft Limited: 

Amendment 39–16570; Docket No. 

FAA–2009–0622; Directorate Identifier 

2009–CE–034–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective February 16, 2011. 

Affected ADs 

(b) This AD revises AD 2009–18–03, 

Amendment 39–15999. 

Applicability 

(c) This AD applies to Pilatus Aircraft Ltd. 

Models PC–6, PC–6–H1, PC–6–H2, PC–6/350, 

PC–6/350–H1, PC–6/350–H2, PC–6/A, PC–6/ 

A–H1, PC–6/A–H2, PC–6/B–H2, PC–6/B1– 

H2, PC–6/B2–H2, PC–6/B2–H4, PC–6/C–H2, 

and PC–6/C1–H2 airplanes, all manufacturer 

serial number (MSN) 101 through 999, and 

MSN 2001 through 2092, certificated in any 

category. 

Note 1: For MSN 2001–2092, these 

airplanes are also identified as Fairchild 

Republic Company PC–6 airplanes, Fairchild 

Industries PC–6 airplanes, Fairchild Heli 

Porter PC–6 airplanes, or Fairchild-Hiller 

Corporation PC–6 airplanes. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Findings of corrosion, wear and cracks in 

the upper wing strut fittings on some PC–6 

aircraft have been reported in the past. It is 

possible that the spherical bearing of the 

wing strut fittings installed in the underwing 

can be loose in the fitting or cannot rotate 

because of corrosion. In this condition, the 

joint cannot function as designed and fatigue 

cracks may then develop. Undetected cracks, 

wear and/or corrosion in this area could 

cause failure of the upper attachment fitting, 

leading to failure of the wing structure and 

subsequent loss of control of the aircraft. 

To address this problem, FOCA published 

AD TM–L Nr. 80.627–6/Index 72–2 and HB– 

2006–400 and EASA published AD 2007– 

0114 to require specific inspections and to 

obtain a fleet status. Since the issuance of AD 

2007–0114, the reported data proved that it 

was necessary to establish and require 

repetitive inspections. 

EASA published Emergency AD 2007– 

0241–E to extend the applicability and to 

require repetitive eddy current and visual 

inspections of the upper wing strut fitting for 

evidence of cracks, wear and/or corrosion 

and examination of the spherical bearing and 

replacement of cracked fittings. Collected 

data received in response to Emergency AD 

2007–0241–E resulted in the issuance of 

EASA AD 2007–0241R1 that permitted 

extending the intervals for the repetitive 

eddy current and visual inspections from 100 

Flight Hours (FH) to 300 FH and from 150 

Flight Cycles (FC) to 450 FC, respectively. In 

addition, oversize bolts were introduced by 

Pilatus PC–6 Service Bulletin (SB) 57–005 R1 

and the fitting replacement procedure was 

adjusted accordingly. 

Based on fatigue test results, EASA AD 

2007–0241R2 was issued to extend the 

repetitive inspection interval to 1100 FH or 

12 calendar months, whichever occurs first, 

and to delete the related flight cycle intervals 

and the requirement for the ‘‘Mild Corrosion 

Severity Zone’’. In addition, some editorial 

changes have been made for reasons of 

standardization and readability. 

Revision 3 of this AD referred to the latest 

revision of the PC–6 Aircraft Maintenance 

Manual (AMM) Chapter 5 limitations which 

have included the same repetitive inspection 

intervals and procedures already mandated 

in the revision 2 of AD 2007–0241. Besides 

the inspections, in the latest revision of the 

PC–6 AMM, the replacement procedures for 

the fittings were included. 

Additionally, EASA AD 2007–0241R3 

introduced the possibility to replace the wing 

strut fitting with a new designed wing strut 

fitting. With this optional part replacement, 

in the repetitive inspection procedure the 

1100 FH interval is deleted so that only 

calendar defined intervals of inspections 

remained applicable. 

The aim of this new revision is to only 

mandate the initial inspection requirement 

and consequently to limit its applicability to 

aeroplanes which are not already in 

mstockstill on DSKH9S0YB1PROD with RULES

Federal Register / Vol. 76, No. 8 / Wednesday, January 12, 2011 / Rules and Regulations 1993 

compliance with EASA AD 2007–0241R3. 

All aeroplanes which are in compliance with 

EASA AD 2007–0241R3 have to follow the 

repetitive inspection requirements as 

described in Pilatus PC–6 AMM Chapter 04– 

00–00, Document Number 01975, Revision 

12 and the Airworthiness Limitations (ALS) 

Document Number 02334 Revision 1 

mandated by EASA AD 2010–0176. 

Therefore the repetitive inspection 

requirements corresponding paragraphs have 

been deleted in this new EASA AD revision. 

The paragraph numbers of EASA AD 2007– 

0241R numbering has been maintained for 

referencing needs. 

This AD requires actions that are intended to 

address the unsafe condition described in the 

MCAI. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) For affected airplanes that have not had 

both wing strut fittings replaced within the 

last 100 hours time-in-service (TIS) before 

September 26, 2007 (the effective date of AD 

2007–19–14), or have not been inspected 

using an eddy current inspection method 

following Pilatus Aircraft Ltd. Pilatus PC–6 

Service Bulletin No. 57–004, dated April 16, 

2007, within the last 100 hours TIS before 

September 26, 2007 (the effective date of AD 

2007–19–14): Before further flight after either 

September 26, 2007 (the effective date of AD 

2007–19–14), or October 1, 2009 (the 

effective date of AD 2009–18–03), visually 

inspect the upper wing strut fittings and 

examine the spherical bearings following the 

Pilatus Aircraft Ltd. Pilatus PC–6 Service 

Bulletin No. 57–005, REV No. 2, dated May 

19, 2008. 

(2) For all affected airplanes: Within 25 

hours TIS after September 26, 2007 (the 

effective date of AD 2007–19–14), or within 

30 days after September 26, 2007 (the 

effective date of AD 2007–19–14), whichever 

occurs first, visually and using eddy current 

methods, inspect the upper wing strut fittings 

and examine the spherical bearings following 

Pilatus Aircraft Ltd. Pilatus PC–6 Service 

Bulletin No. 57–005, REV No. 2, dated May 

19, 2008. 

(3) You may also take ‘‘unless already 

done’’ credit for any inspection specified in 

paragraphs (f)(1) or (f)(2) of this AD if done 

before October 1, 2009 (the effective date 

retained from AD 2009–18–03) following 

Pilatus Aircraft Ltd. Pilatus PC–6 Service 

Bulletin No. 57–005, dated August 30, 2007; 

or Pilatus Aircraft Ltd. Pilatus PC–6 Service 

Bulletin No. 57–005, REV No. 1, dated 

November 19, 2007. 

(4) For all affected airplanes: If during any 

inspection required by paragraphs (f)(1) or 

(f)(2) of this AD you find cracks in the upper 

wing strut fitting or the spherical bearing is 

not in conformity, before further flight, 

replace the cracked upper wing strut fitting 

and/or the nonconforming spherical bearing 

following Chapter 57–00–02 of Pilatus 

Aircraft Ltd. Pilatus PC–6 Aircraft 

Maintenance Manual, dated November 30, 

2008. 

Note 1: AD 2011–01–14 requires the 

incorporation of the updated maintenance 

requirements into the airworthiness 

limitations section of the instructions for 

continued airworthiness. Those updated 

maintenance requirements include the 

repetitive inspections for the wing strut 

fittings and the spherical bearings. This 

revised AD removes those repetitive 

inspections. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

Attn: Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4059; fax: (816) 329– 

4090. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(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. 

(3) Reporting Requirements: For any 

reporting requirement in 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. 

Related Information 

(h) Refer to MCAI EASA AD No.: 2007– 

0241R4, dated August 31, 2010; Pilatus 

Aircraft Ltd. Pilatus PC–6 Service Bulletin 

No. 57–005, REV No. 2, dated May 19, 2008; 

Pilatus Aircraft Ltd. Pilatus PC–6 Service 

Bulletin No. 57–005, REV No. 1, dated 

November 19, 2007; Pilatus Aircraft Ltd. 

Pilatus PC–6 Service Bulletin No. 57–005, 

dated August 30, 2007; Pilatus Aircraft Ltd. 

Pilatus PC–6 Service Bulletin No. 57–004, 

dated April 16, 2007; and Chapter 57–00–02 

of Pilatus Aircraft Ltd. Pilatus PC–6 Aircraft 

Maintenance Manual, dated November 30, 

2008, for related information. 

Material Incorporated by Reference 

(h) You must use Pilatus Aircraft Ltd. 

Pilatus PC–6 Service Bulletin No. 57–005, 

REV No. 2, dated May 19, 2008; and Chapter 

57–00–02 of Pilatus Aircraft Ltd. Pilatus PC– 

6 Aircraft Maintenance Manual, dated 

November 30, 2008 (referenced as revision 9 

in EASA AD No.: 2007–0241R3), to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

(1) On October 1, 2009 (74 FR 43636, 

August 27, 2009), the Director of the Federal 

Register previously approved the 

incorporation by reference of Pilatus Aircraft 

Ltd. Pilatus PC–6 Service Bulletin No. 57– 

005, REV No. 2, dated May 19, 2008; and 

Chapter 57–00–02 of Pilatus Aircraft Ltd. 

Pilatus PC–6 Aircraft Maintenance Manual, 

dated November 30, 2008 (referenced as 

revision 9 in EASA AD No.: 2007–0241R3). 

(2) For service information identified in 

this AD, contact PILATUS AIRCRAFT LTD., 

Customer Service Manager, CH–6371 

STANS, Switzerland; telephone: +41 (0) 41 

619 65 01; fax: +41 (0) 41 619 65 76; Internet: 

http://www.pilatus-aircraft.com. 

(3) You may review copies of the 

referenced service information at the FAA, 

Small Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call 816–329–4148. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call (202) 741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Kansas City, Missouri, on 

December 28, 2010. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2010–33333 Filed 1–11–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0549; Directorate 

Identifier 2010–NM–109–AD; Amendment 

39–16573; AD 2011–01–16] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model DC–9–81 (MD–81), 

DC–9–82 (MD–82), DC–9–83 (MD–83), 

DC–9–87 (MD–87), and MD–88 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

mstockstill on DSKH9S0YB1PROD with RULES