Federal Register / Vol. 73, No. 157 / Wednesday, August 13, 2008 / Rules and Regulations 47039 

Alternative Methods of Compliance 

(AMOCs) 

(v)(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested in accordance with the 

procedures found in 14 CFR 39.19. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. 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. 

(3) An AMOC that provides an acceptable 

level of safety shall be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 94–15–06 for airplane 

line numbers 630 through 814 inclusive are 

approved as AMOCs for the corresponding 

provisions of this AD if the AMOC does not 

involve using the existing sliding probe 

HFEC skin inspection method specified in 

Boeing Service Bulletin 747–53A2312, 

Revision 2, dated October 8, 1992, or an 

earlier version. In addition, the provisions of 

paragraph (r) of this AD must be applied to 

AMOCs approved previously in accordance 

with AD 94–15–06, where applicable. 

(5) AMOCs approved previously in 

accordance with AD 94–15–06 for airplane 

line numbers 201 through 629 inclusive are 

approved as AMOCs for the corresponding 

provisions of this AD. In addition, the 

provisions of paragraph (r) of this AD must 

be applied to AMOCs approved previously in 

accordance with AD 94–15–06, where 

applicable. 

Material Incorporated by Reference 

(w) You must use Boeing Alert Service 

Bulletin 747–53A2312, dated June 12, 1989; 

Boeing Service Bulletin 747–53A2312, 

Revision 1, including ‘‘Addendum,’’ dated 

March 29, 1990; Boeing Service Bulletin 747–

53A2312, including the ‘‘Addendum,’’

Revision 2, dated October 8, 1992; or Boeing 

Service Bulletin 747–53A2312, Revision 3, 

dated February 8, 2007; as applicable; to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. (The 

document number and date of Boeing Alert 

Service Bulletin 747–53A2312, dated June 

12, 1989, are identified only on the first page 

of the document; no other page of the 

document contains this information.) 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin 747–53A2312, 

dated June 12, 1989; Boeing Service Bulletin 

747–53A2312, Revision 1, including 

‘‘Addendum,’’ dated March 29, 1990; and 

Boeing Service Bulletin 747–53A2312, 

Revision 3, dated February 8, 2007; in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) On August 24, 1994 (59 FR 37659, July 

25, 1994), the Director of the Federal Register 

approved the incorporation by reference of 

Boeing Service Bulletin 747–53A2312, 

including the ‘‘Addendum,’’ Revision 2, 

dated October 8, 1992. 

(3) Contact Boeing Commercial Airplanes, 

P.O. Box 3707, Seattle, Washington 98124–

2207, for a copy of this service information. 

You may review copies at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on July 23, 

2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–17776 Filed 8–12–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0626 Directorate 

Identifier 2008–CE–035–AD; Amendment 

39–15637; AD 2008–16–19] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Model PC–6 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

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: 

This Airworthiness Directive (AD) is 

prompted due to the discovery of loose selflocking stop nuts Part Number (P/N) 

938.07.65.105 in the tail landing gear fastener 

assemblies of some PC–6 aircraft. 

It is believed that this occurrence could 

also exist in other fastener assemblies using 

nuts P/N 938.07.65.105 at various identified 

locations in the aircraft. 

If left uncorrected, the identified 

assemblies may become loose and not 

function as designed and could lead to 

hazardous situations. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

September 17, 2008. 

On September 17, 2008, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

Document 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 FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 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 June 9, 2008 (73 FR 32497). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

This Airworthiness Directive (AD) is 

prompted due to the discovery of loose selflocking stop nuts Part Number (P/N) 

938.07.65.105 in the tail landing gear fastener 

assemblies of some PC–6 aircraft. 

It is believed that this occurrence could 

also exist in other fastener assemblies using 

nuts P/N 938.07.65.105 at various identified 

locations in the aircraft. 

If left uncorrected, the identified 

assemblies may become loose and not 

function as designed and could lead to 

hazardous situations. 

In order to prevent those conditions, the 

present AD requires you to replace selflocking stop nuts P/N 938.07.65.105 from the 

Tail Landing Gear Assembly, the Parachute 

Cable Assembly, the Water Tank Assembly, 

the Cable Tensioner Assembly, the Fuel 

Filter Assembly, the Hydraulic Pump 

Assembly and the Engine Mounts Assembly 

in accordance with Pilatus PC–6 Service 

Bulletin No. 53–002 Revision 2. 

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. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 


hsrobinson on PROD1PC76 with RULES
47040 Federal Register / Vol. 73, No. 157 / Wednesday, August 13, 2008 / Rules and Regulations 

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 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

Costs of Compliance 

Based on the service information, 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 basic 

requirements of this AD. The average 

labor rate is $80 per work-hour. 

Required parts will cost about $310 per 

product. 

Based on these figures, we estimate 

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

to be $43,500, or $870 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 

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 adding 

the following new AD: 

2008–16–19 Pilatus Aircraft Ltd.: 

Amendment 39–15637; Docket No. 

FAA–2008–0626; Directorate Identifier 

2008–CE–035–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 17, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to 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, 

manufacturer serial numbers (MSN) MSN 

101 through MSN 949 and MSN 2001 

through MSN 2092, certificated in any 

category. 

Note 1: These airplanes may also be 

identified as Fairchild Republic Company 

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 53: Fuselage. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

This Airworthiness Directive (AD) is 

prompted due to the discovery of loose selflocking stop nuts Part Number (P/N) 

938.07.65.105 in the tail landing gear fastener 

assemblies of some PC–6 aircraft. 

It is believed that this occurrence could 

also exist in other fastener assemblies using 

nuts P/N 938.07.65.105 at various identified 

locations in the aircraft. 

If left uncorrected, the identified 

assemblies may become loose and not 

function as designed and could lead to 

hazardous situations. 

In order to prevent those conditions, the 

present AD requires you replace self-locking 

stop nuts P/N 938.07.65.105 from the Tail 

Landing Gear Assembly, the Parachute Cable 

Assembly, the Water Tank Assembly, the 

Cable Tensioner Assembly, the Fuel Filter 

Assembly, the Hydraulic Pump Assembly 

and the Engine Mounts Assembly in 

accordance with Pilatus PC–6 Service 

Bulletin No. 53–002 Revision 2. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within the next 12 months after 

September 17, 2008 (the effective date of this 

AD), inspect and modify the fastener 

assemblies as instructed in paragraph 3 of 

Pilatus Aircraft Ltd. Pilatus PC–6 Service 

Bulletin No. 53–002, Revision No. 2, dated 

September 24, 2007. 

(2) As of September 17, 2008 (the effective 

date of this AD), no person shall install on 

any PC–6 series aircraft, water tank 

assemblies and hydraulic pump assemblies, 

unless they have been previously modified 

following paragraph 4 of Pilatus Aircraft Ltd. 

Pilatus PC–6 Service Bulletin No. 53–002, 

Revision No. 2, dated September 24, 2007. 

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; 


hsrobinson on PROD1PC76 with RULES
Federal Register / Vol. 73, No. 157 / Wednesday, August 13, 2008 / Rules and Regulations 47041 

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, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency EASA AD No.: 2008–0083, 

dated May 5, 2008; and Pilatus Aircraft Ltd. 

Pilatus PC–6 Service Bulletin No. 53–002, 

Revision No. 2, dated September 24, 2007, for 

related information. 

Material Incorporated by Reference 

(i) You must use Pilatus Aircraft Ltd. 

Pilatus PC–6 Service Bulletin No. 53–002, 

Revision No. 2, dated September 24, 2007, 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 Pilatus Aircraft Ltd., 

Customer Liaison Manager, CH–6371 

STANS, Switzerland; telephone: +41 41 619 

65 80; fax: +41 41 619 65 76; e-mail: 

fodermatt@pilatus-aircraft.com. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Room 506, Kansas City, 

Missouri 64106; or 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/ 

cfr/ibr-locations.html. 

Issued in Kansas City, Missouri, on August 

1, 2008. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–18236 Filed 8–12–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0685 Directorate 

Identifier 2008–CE–037–AD; Amendment 

39–15638; AD 2008–16–20] 

RIN 2120–AA64 

Airworthiness Directives; Diamond 

Aircraft Industries GmbH Model DA 42 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

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: 

The original designed bellcrank for the 

aileron control system in the wing needed to 

be installed with slightly bent rod ends 

during production of the aircraft to avoid 

friction and possible chafing. In addition to 

being a nonpreferable production practice, 

this creates the risk of replacement parts 

being installed during subsequent in-service 

maintenance without being bent or not being 

bent correctly. This condition, if not detected 

and corrected, could lead to chafing damage 

of the aileron control system and consequent 

loss of control of the aircraft. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

September 17, 2008. 

On September 17, 2008, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

Document 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 FURTHER INFORMATION CONTACT: 

Sarjapur Nagarajan, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329–

4145; 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 June 23, 2008 (73 FR 35361). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

The original designed bellcrank for the 

aileron control system in the wing needed to 

be installed with slightly bent rod ends 

during production of the aircraft to avoid 

friction and possible chafing. In addition to 

being a nonpreferable production practice, 

this creates the risk of replacement parts 

being installed during subsequent in-service 

maintenance without being bent or not being 

bent correctly. This condition, if not detected 

and corrected, could lead to chafing damage 

of the aileron control system and consequent 

loss of control of the aircraft. 

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. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

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 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD will affect 156 

products of U.S. registry. We also 

estimate that it will take about 3 workhours per product to comply with basic 

requirements of this AD. The average 

labor rate is $80 per work-hour. 

Required parts will cost about $0 per 

product (warranty credit given by 

manufacturer) per product. Where the 

service information lists required parts 

costs that are covered under warranty, 

we have assumed that there will be no 


hsrobinson on PROD1PC76 with RULES