Federal Register / Vol. 76, No. 8 / Wednesday, January 12, 2011 / Rules and Regulations 1985 

self-adhering high-temperature electrical 

insulation tape on the wire assemblies, 

install wire assembly support brackets, route 

wire assemblies, install extruded channel 

wire supports, and install a wire protection 

bracket, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD11–28A124, Revision 1, 

dated August 24, 2010. 

(3) For airplanes in Group 2, Configuration 

1: If no damage is found, before further flight, 

install wire assembly support brackets, route 

wire assemblies, install extruded channel 

wire supports, and install a wire protection 

bracket, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD11–28A124, Revision 1, 

dated August 24, 2010. 

(4) For airplanes in Group 2, Configuration 

1: If damage is found, before further flight, 

repair or replace the wire assemblies, install 

wire assembly support brackets, route wire 

assemblies, install extruded channel wire 

supports, and install a wire protection 

bracket, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD11–28A124, Revision 1, 

dated August 24, 2010. 

(h) For airplanes in Group 1, Configuration 

2: Within 60 months after the effective date 

of this AD, do a general visual inspection for 

correct installation of the self-adhering hightemperature electrical insulation tape, and 

change the wire supports, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin MD11–28A124, 

Revision 1, dated August 24, 2010. If the selfadhering high-temperature electrical 

insulation tape is installed incorrectly, before 

further flight, adjust the tape installation to 

achieve the correct dimensions, in 

accordance with Figure 1 of Boeing Alert 

Service Bulletin MD11–28A124, Revision 1, 

dated August 24, 2010. 

(i) For airplanes in Group 2, Configuration 

2: Within 60 months after the effective date 

of this AD, change the wire supports, in 

accordance with Figure 2 of Boeing Alert 

Service Bulletin MD11–28A124, Revision 1, 

dated August 24, 2010. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) 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. 

Related Information 

(k) For more information about this AD, 

contact Serj Harutunian, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, Los 

Angeles Aircraft Certification Office, 3960 

Paramount Boulevard, Lakewood, California 

90712–4137; phone: (562) 627–5254; fax: 

(562) 627–5210; e-mail: 

Serj.Harutunian@faa.gov. 

Material Incorporated by Reference 

(l) You must use Boeing Alert Service 

Bulletin MD11–28A124, Revision 1, dated 

August 24, 2010, to do the actions required 

by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information, under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, California 90846– 

0001; telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.boecom@boeing.com; Internet https:// 

www.myboeingfleet.com. 

(3) 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. 

(4) 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 

3, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–271 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–2010–0225; Directorate 

Identifier 2009–NM–203–AD; Amendment 

39–16525; AD 2010–24–06] 

RIN 2120–AA64 

Airworthiness Directives; Short 

Brothers PLC Model SD3 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) 

that applies to the products listed above. 

This AD results from mandatory 

continuing airworthiness information 

(MCAI) issued by an airworthiness 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as 

Subsequent to accidents involving Fuel 

Tank System explosions in flight * * * and 

on ground, * * * Special Federal Aviation 

Regulation 88 (SFAR88) * * * required a 

safety review of the aircraft Fuel Tank 

System * * *. 

* * * * * 

Fuel Airworthiness Limitations are items 

arising from a systems safety analysis that 

have been shown to have failure mode(s) 

associated with an ‘unsafe condition’ * * *. 

These are identified in Failure Conditions for 

which an unacceptable probability of ignition 

risk could exist if specific tasks and/or 

practices are not performed in accordance 

with the manufacturers’ requirements. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

February 16, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of February 16, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of July 21, 2006 (71 FR 

34801, June 16, 2006). 

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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1175; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (NPRM) to amend 

14 CFR part 39 to include an AD that 

would apply to the specified products. 

That supplemental NPRM was 

published in the Federal Register on 

August 4, 2010 (75 FR 46864), and 

proposed to supersede AD 2006–12–18, 

Amendment 39–14644 (71 FR 34801, 

June 16, 2006). That NPRM proposed to 

require revising the airplane flight 

manual (AFM); revising the 

Airworthiness Limitation (AWL) 

section; doing a resistance check, 

inspection, and jumper installation; and 

revising the AWL section. The MCAI 

states: 

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Subsequent to accidents involving Fuel 

Tank System explosions in flight * * * and 

on ground, the FAA published Special 

Federal Aviation Regulation 88 (SFAR88) in 

June 2001. SFAR 88 required a safety review 

of the aircraft Fuel Tank System to determine 

that the design meets the requirements of 

FAR [Federal Aviation Regulation] § 25.901 

and § 25.981(a) and (b). 

A similar regulation has been 

recommended by the JAA [Joint Aviation 

Authorities] to the European National 

Aviation Authorities in JAA letter 04/00/02/ 

07/03–L024 of 3 February 2003. The review 

was requested to be mandated by NAA’s 

[National Airworthiness Authorities] using 

JAR [Joint Aviation Requirement] § 25.901(c), 

§ 25.1309. 

In August 2005 EASA [European Aviation 

Safety Agency] published a policy statement 

on the process for developing instructions for 

maintenance and inspection of Fuel Tank 

System ignition source prevention (EASA D 

2005/CPRO, www.easa.eu.int/home/ 

cert_policy_statements_en.html) that also 

included the EASA expectations with regard 

to compliance times of the corrective actions 

on the unsafe and the not unsafe part of the 

harmonised design review results. On a 

global scale the TC [type certificate] holders 

committed themselves to the EASA 

published compliance dates (see EASA 

policy statement). The EASA policy 

statement has been revised in March 2006: 

The date of 31–12–2005 for the unsafe related 

actions has now been set at 01–07–2006. 

Fuel Airworthiness Limitations are items 

arising from a systems safety analysis that 

have been shown to have failure mode(s) 

associated with an ‘unsafe condition’ as 

defined in FAA’s memo 2003–112–15 ‘SFAR 

88—Mandatory Action Decision Criteria’. 

These are identified in Failure Conditions for 

which an unacceptable probability of ignition 

risk could exist if specific tasks and/or 

practices are not performed in accordance 

with the manufacturers’ requirements. 

This EASA Airworthiness Directive 

mandates the Fuel System Airworthiness 

Limitations, comprising maintenance/ 

inspection tasks and Critical Design Control 

Configuration Limitations (CDCCL) for the 

type of aircraft, that resulted from the design 

reviews and the JAA recommendation and 

EASA policy statement mentioned above. 

Revision History: PAD [proposed 

airworthiness directive] 06–018R1 has been 

issued to endorse comments received for 

PAD 06–018 and due to the change of the 

EASA policy statement on fuel tank safety on 

March 2006. 

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 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Explanation of Changes to This AD 

We have revised Table 1 of this AD 

to indicate the appropriate AFM for the 

identified airplane models. We have 

also added new paragraph (l) to this AD 

(and have reidentified subsequent 

paragraphs accordingly) to give credit to 

operators that might have included 

Shorts Advance Amendment Bulletin 

1/2004, dated 7/13/04, into the incorrect 

AFM before the effective date of this 

AD. We have determined that the 

content of Shorts Advance Amendment 

Bulletin 1/2004 to AFM SB.5.2 and 

Shorts Advance Amendment Bulletin 

1/2004 to AFM SB.6.2 is identical, 

except for the AFM number shown on 

the top of the document pages. 

Therefore, if an operator inserted the 

advance amendment bulletin intended 

for AFM SB.5.2 into AFM SB.6.2 or vise 

versa, before the effective date of this 

AD, the intent of the AFM revision 

required by paragraph (g) of this AD has 

been met, and is, therefore, acceptable 

for compliance with that requirement. 

Conclusion 

We reviewed the available data 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 a U.S. 

court of law. 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 

MCAI in order to follow our FAA 

policies. Any such differences are 

described in a separate paragraph of the 

AD. These requirements, if any, take 

precedence over the actions copied from 

the MCAI. 

Costs of Compliance 

We estimate that this AD will affect 

54 products of U.S. registry. 

The actions that are required by AD 

2006–12–18 and retained in this AD 

take about 41 work-hours per product, 

at an average labor rate of $85 per work 

hour. Required parts cost about $10 per 

product. Based on these figures, the 

estimated cost of the currently required 

actions is $3,495 per product. 

We estimate that it would take about 

1 work-hour 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 $4,590, or $85 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 that 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 Operations office 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 Operations office (telephone 

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Federal Register / Vol. 76, No. 8 / Wednesday, January 12, 2011 / Rules and Regulations 1987 

(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 39–14644 (71 FR 

34801, June 16, 2006) and adding the 

following new AD: 

2010–24–06 Short Brothers PLC: 

Amendment 39–16525. Docket No. 

FAA–2010–0225; Directorate Identifier 

2009–NM–203–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective February 16, 2011. 

Affected ADs 

(b) This AD supersedes AD 2006–12–18, 

Amendment 39–14644. 

Applicability 

(c) This AD applies to all Short Brothers 

PLC Model SD3–60 SHERPA, SD3–SHERPA, 

SD3–30, and SD3–60 airplanes, certificated 

in any category. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (m) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued damage tolerance of the affected 

structure. The FAA has provided guidance 

for this determination in Advisory Circular 

(AC) 25–1529. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Subsequent to accidents involving Fuel 

Tank System explosions in flight * * * and 

on ground, the FAA published Special 

Federal Aviation Regulation 88 (SFAR88) in 

June 2001. SFAR 88 required a safety review 

of the aircraft Fuel Tank System to determine 

that the design meets the requirements of 

FAR [Federal Aviation Regulation] § 25.901 

and § 25.981(a) and (b). 

A similar regulation has been 

recommended by the JAA [Joint Aviation 

Authorities] to the European National 

Aviation Authorities in JAA letter 04/00/02/ 

07/03–L024 of 3 February 2003. The review 

was requested to be mandated by NAA’s 

[National Airworthiness Authorities] using 

JAR [Joint Aviation Requirement] § 25.901(c), 

§ 25.1309. 

In August 2005 EASA [European Aviation 

Safety Agency] published a policy statement 

on the process for developing instructions for 

maintenance and inspection of Fuel Tank 

System ignition source prevention (EASA D 

2005/CPRO, http://www.easa.eu.int/home/ 

cert_policy_statements_en.html) that also 

included the EASA expectations with regard 

to compliance times of the corrective actions 

on the unsafe and the not unsafe part of the 

harmonised design review results. On a 

global scale the TC [type certificate] holders 

committed themselves to the EASA 

published compliance dates (see EASA 

policy statement). The EASA policy 

statement has been revised in March 2006: 

The date of 31–12–2005 for the unsafe related 

actions has now been set at 01–07–2006. 

Fuel Airworthiness Limitations are items 

arising from a systems safety analysis that 

have been shown to have failure mode(s) 

associated with an ‘unsafe condition’ as 

defined in FAA’s memo 2003–112–15 ‘SFAR 

88—Mandatory Action Decision Criteria’. 

These are identified in Failure Conditions for 

which an unacceptable probability of ignition 

risk could exist if specific tasks and/or 

practices are not performed in accordance 

with the manufacturers’ requirements. 

This EASA Airworthiness Directive 

mandates the Fuel System Airworthiness 

Limitations, comprising maintenance/ 

inspection tasks and Critical Design Control 

Configuration Limitations (CDCCL) for the 

type of aircraft, that resulted from the design 

reviews and the JAA recommendation and 

EASA policy statement mentioned above. 

Revision History: PAD [proposed 

airworthiness directive] 06–018R1 has been 

issued to endorse comments received for 

PAD 06–018 and due to the change of the 

EASA policy statement on fuel tank safety on 

March 2006. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2006– 

12–18 

Revision of Airplane Flight Manual (AFM) 

(g) Within 30 days after July 21, 2006 (the 

effective date of AD 2006–12–18), revise the 

Limitations and Normal Procedures sections 

of the AFMs as specified in Table 1 of this 

AD to include the information in the 

applicable Shorts advance amendment 

bulletins as specified in Table 1 of this AD. 

The advance amendment bulletins address 

operation during icing conditions and fuel 

system failures. Thereafter, operate the 

airplane according to the limitations and 

procedures in the applicable advance 

amendment bulletin. 

Note 2: The requirements of paragraph (g) 

of this AD may be done by inserting a copy 

of the applicable advance amendment 

bulletin into the AFM. When the applicable 

advance amendment bulletin has been 

included in general revisions of the AFM, the 

general revisions may be inserted into the 

AFM and the advance amendment bulletin 

may be removed, provided the relevant 

information in the general revision is 

identical to that in the advance amendment 

bulletin. 

TABLE 1—AFM REVISIONS

Airplane model— Shorts advance amendment bulletin— AFM— 

SD3–30 airplanes .............................................. 1/2004, dated July 13, 2004 ............................ SBH.3.2, SBH.3.3, SBH.3.6, SBH.3.7, 

SBH.3.8, and SB.3.9. 

SD3–60 airplanes .............................................. 1/2004, dated July 13, 2004 ............................ SB.4.3, SB.4.6, and SB.4.8. 

SD3–60 SHERPA airplanes .............................. 1/2004, dated July 13, 2004 ............................ SB.6.2. 

SD3–SHERPA airplanes ................................... 1/2004, dated July 13, 2004 ............................ SB.5.2. 

Revision of Airworthiness Limitation (AWL) 

Section 

(h) Within 180 days after July 21, 2006: 

Revise the AWL section of the Instructions 

for Continued Airworthiness by 

incorporating airplane maintenance manual 

(AMM) Sections 5–20–01 and 5–20–02 as 

introduced by the Shorts temporary revisions 

(TR) specified in Table 2 of this AD into the 

AWL section of the AMMs for the airplane 

models specified in Table 2 of this AD, 

except as required by paragraph (j) of this 

AD. Thereafter, except as provided by 

paragraph (m)(1) of this AD, no alternative 

structural inspection intervals may be 

approved for the longitudinal skin joints in 

the fuselage shell. 

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Note 3: The requirements of paragraph (h) 

of this AD may be done by inserting a copy 

of the applicable TR into the applicable 

AMM. When the TR has been included in 

general revisions of the AMM, the general 

revisions may be inserted in the AMM and 

the TR may be removed, provided the 

relevant information in the general revision 

is identical to that in the TR. 

TABLE 2—AMM TEMPORARY REVISIONS

Airplane model— Temporary revision— Date— AMM— 

SD3–30 airplanes .......................... TR330–AMM–13 ........................... June 21, 2004 ............................... SD3–30 AMM. 

SD3–30 airplanes .......................... TR330–AMM–14 ........................... June 21, 2004 ............................... SD3–30 AMM. 

SD3–60 airplanes .......................... TR360–AMM–33 ........................... July 27, 2004 ................................ SD3–60 AMM. 

SD3–60 airplanes .......................... TR360–AMM–34 ........................... July 27, 2004 ................................ SD3–60 AMM. 

SD3–60 SHERPA airplanes .......... TRSD360S–AMM–14 ................... July 29, 2004 ................................ SD3–60 SHERPA AMM. 

SD3–60 SHERPA airplanes .......... TRSD360S–AMM–15 ................... July 29, 2004 ................................ SD3–60 SHERPA AMM. 

SD3–SHERPA airplanes ................ TRSD3S–AMM–15 ....................... July 28, 2004 ................................ SD3 SHERPA AMM. 

SD3–SHERPA airplanes ................ TRSD3S–AMM–16 ....................... July 28, 2004 ................................ SD3 SHERPA AMM. 

Resistance Check, Inspection, and Jumper 

Installation 

(i) Within 180 days after July 21, 2006: 

Perform the insulation resistance check, 

general visual inspections, and bonding 

jumper wire installations; in accordance with 

Shorts Service Bulletin SD330–28–37, 

SD360–28–23, SD360 SHERPA–28–3, or SD3 

SHERPA–28–2; all dated June 2004; as 

applicable. If any defect or damage is 

discovered during any inspection or check 

required by this AD, before further flight, 

repair the defect or damage using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; the Civil Aviation 

Authority (CAA) (or its delegated agent); or 

EASA (or its delegated agent). 

Note 4: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’ 

New Requirements of This AD 

Revision of AWL Section: New Limitations 

and CDCCLs 

(j) Within 90 days after the effective date 

of this AD: Revise the AWL section of the 

Instructions for Continued Airworthiness by 

incorporating maintenance manual Sections 

5–20–01 and 5–20–02 as introduced by the 

Bombardier and Shorts TRs specified in 

Table 3 of this AD into the AWL section of 

the maintenance manuals for the airplane 

models specified in Table 3 of this AD. Doing 

this revision terminates the requirement to 

incorporate the temporary revisions specified 

in paragraph (h) of this AD. After doing this 

revision the temporary revisions required by 

paragraph (h) of this AD may be removed. 

TABLE 3—NEWLY REQUIRED MAINTENANCE MANUAL TEMPORARY REVISIONS

Model— Temporary revision— Date— Manual— 

SD3–30 airplanes .......................... Shorts TR TR330–AMM–35 ......... June 6, 2006 ................................. Shorts SD3–30 Maintenance 

Manual (MM). 

SD3–30 airplanes .......................... Shorts TR TR330–AMM–36 ......... June 6, 2006 ................................. Shorts SD3–30 MM. 

SD3–60 airplanes .......................... Bombardier TR TR360–AMM–55 November 11, 2005 ...................... Bombardier SD3–60 AMM. 

SD3–60 airplanes .......................... Bombardier TR TR360–AMM–56 November 11, 2005 ...................... Bombardier SD3–60 AMM. 

SD3–60 SHERPA airplanes .......... Shorts TR TRSD360S–AMM–35 .. June 27, 2006 ............................... Shorts SD3–60 SHERPA MM. 

SD3–60 SHERPA airplanes .......... Shorts TR TRSD360S–AMM–36 .. June 27, 2006 ............................... Shorts SD3–60 SHERPA MM. 

SD3–SHERPA airplanes ................ Shorts TR TRSD3S–AMM–36 ...... June 19, 2006 ............................... Shorts SD3–SHERPA MM. 

SD3–SHERPA airplanes ................ Shorts TR TRSD3S–AMM–37 ...... June 19, 2006 ............................... Shorts SD3–SHERPA MM. 

Note 5: The requirements of paragraph (j) 

of this AD may be done by inserting a copy 

of the applicable TR into the applicable 

maintenance manual. When the TR has been 

included in general revisions of the AMM, 

the general revisions may be inserted in the 

AMM and the TR may be removed, provided 

the relevant information in the general 

revision is identical to that in the TR. 

(k) After accomplishing the actions 

specified in paragraph (j) of this AD, no 

alternative inspections, inspection intervals, 

or CDCCLs may be used unless the 

inspections, intervals, or CDCCLs are 

approved as an alternative method of 

compliance (AMOC), in accordance with the 

procedures specified in paragraph (m) of this 

AD. 

Explanation of CDCCL Requirements 

Note 6: Notwithstanding any other 

maintenance or operational requirements, 

components that have been identified as 

airworthy or installed on the affected 

airplanes before the revision of the AMM, as 

required by paragraph (h) or (j) of this AD, 

do not need to be reworked in accordance 

with the CDCCLs. However, once the AMM 

has been revised, future maintenance actions 

on these components must be done in 

accordance with the CDCCLs. 

Credit for Actions Accomplished in 

Accordance With Other Service Information 

(l) Revising the AFM, as required by 

paragraph (g) of this AD, by inserting Shorts 

Advance Amendment Bulletin 1/2004, dated 

7/13/04, for Model SD3–60 Sherpa airplanes, 

into AFM SB.5.2; or Shorts Advance 

Amendment Bulletin 1/2004, dated 7/13/04, 

for Model SD3-sherpa airplanes, into AFM 

SB.6.2; before the effective date of this AD is 

acceptable for compliance with the AFM 

revision required by paragraph (g) of this AD. 

FAA AD Differences 

Note 7: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(m) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: Todd Thompson, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1175; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

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Federal Register / Vol. 76, No. 8 / Wednesday, January 12, 2011 / Rules and Regulations 1989 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference 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. 

(3) Reporting Requirements: 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 

(n) Refer to MCAI EASA Airworthiness 

Directive 2006–0198, dated July 11, 2006; 

Shorts Service Bulletins SD330–28–37, 

SD360–28–23, SD360 SHERPA–28–3, and 

SD3 SHERPA–28–2, all dated June 2004; and 

the service information listed in Tables 1, 2, 

and 3 of this AD; for related information. 

Material Incorporated by Reference 

(o) You must use the service information 

contained in Table 4 of this AD, as 

applicable, to do the actions required by this 

AD, unless the AD specifies otherwise. 

TABLE 4—ALL MATERIAL 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 TR330–AMM–13 .................................... June 21, 2004 .................................................. Shorts SD3–30 Airplane Maintenance Manual 

(AMM). 

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

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

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

Shorts TRSD360S–AMM–14 ............................. July 29, 2004 .................................................... Shorts SD3–60 SHERPA AMM. 

Shorts TRSD360S–AMM–15 ............................. July 29, 2004 .................................................... Shorts SD3–60 SHERPA AMM. 

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

Shorts TRSD3S–AMM–16 ................................. July 28, 2004 .................................................... Shorts 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. 

Shorts TR TR330–AMM–35 .............................. June 6, 2006 .................................................... Shorts SD3–30 Maintenance Manual (MM). 

Shorts TR TR330–AMM–36 .............................. June 6, 2006 .................................................... Shorts SD3–30 MM. 

Bombardier TR TR360–AMM–55 ...................... November 11, 2005 ......................................... Bombardier SD3–60 AMM. 

Bombardier TR TR360–AMM–56 ...................... November 11, 2005 ......................................... Bombardier SD3–60 AMM. 

Shorts TR TRSD360S–AMM–35 ....................... June 27, 2006 .................................................. Shorts SD3–60 SHERPA MM. 

Shorts TR TRSD360S–AMM–36 ....................... June 27, 2006 .................................................. Shorts SD3–60 SHERPA MM. 

Shorts TR TRSD3S–AMM–36 ........................... June 19, 2006 .................................................. Shorts SD3–SHERPA MM. 

Shorts TR TRSD3S–AMM–37 ........................... June 19, 2006 .................................................. Shorts SD3–SHERPA MM. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in Table 5 

of this AD under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

TABLE 5—NEW MATERIAL INCORPORATED BY REFERENCE

Document Date Manual 

Shorts TR TR330–AMM–35 .............................. June 6, 2006 .................................................... Shorts SD3–30 MM. 

Shorts TR TR330–AMM–36 .............................. June 6, 2006 .................................................... Shorts SD3–30 MM. 

Bombardier TR TR360–AMM–55 ...................... November 11, 2005 ......................................... Bombardier SD3–60 AMM. 

Bombardier TR TR360–AMM–56 ...................... November 11, 2005 ......................................... Bombardier SD3–60 AMM. 

Shorts TR TRSD360S–AMM–35 ....................... June 27, 2006 .................................................. Shorts SD3–60 SHERPA MM. 

Shorts TR TRSD360S–AMM–36 ....................... June 27, 2006 .................................................. Shorts SD3–60 SHERPA MM. 

Shorts TR TRSD3S–AMM–36 ........................... June 19, 2006 .................................................. Shorts SD3–SHERPA MM. 

Shorts TR TRSD3S–AMM–37 ........................... June 19, 2006 .................................................. Shorts SD3–SHERPA MM. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of the service information 

contained in Table 6 of this AD on July 21, 

2006 (71 FR 34801, June 16, 2006). 

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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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