Federal Register / Vol. 70, No. 206 / Wednesday, October 26, 2005 / Rules and Regulations 61723 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

written data, views, or arguments 

regarding this AD. Send your comments 

to an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2005–22757; 

Directorate Identifier 2005–SW–32–AD’’

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the AD. We will consider all comments 

received by the closing date and may 

amend the AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of our docket web site, 

you can find and read the comments to 

any of our dockets, including the name 

of the individual who sent the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Regulatory Findings 

We have 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 the regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

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

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD. See the DMS to examine the 

economic evaluation. 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by adding 

a new airworthiness directive to read as 

follows: 

2005–22–01 Sikorsky Aircraft Corporation: 

Amendment 39–14345. Docket No. 

FAA–2005–22757; Directorate Identifier 

2005–SW–32–AD. 

Applicability: Model S–76A, B, and C, with 

a main rotor hub pilot fitting (pilot fitting), 

part number (P/N) 76103–08003–101, with 

1500 or more hours time-in-service (TIS), 

installed, certificated in any category. 

Compliance: Required as indicated. 

To prevent failure of a bifilar lug, damage 

to the main rotor system, and subsequent loss 

of control of the helicopter, accomplish the 

following: 

(a) Within 50 hours TIS, and thereafter at 

intervals not to exceed 50 hours TIS, inspect 

the lower bifilar arm assembly for a crack in 

the lug attachment area. Conduct the 

inspection of the lower bifilar arm assembly 

by following the Accomplishment 

Instructions, paragraph 3.A.(1) through 

3.A.(6), of Sikorsky Alert Service Bulletin No. 

76–65–62, dated December 14, 2004 (ASB). 

(1) If you find a crack on any bifilar arm 

assembly lug, before further flight, replace 

the bifilar arm assembly with an airworthy 

bifilar arm assembly. 

(2) If no crack is found at the initial 

inspection, perform a one-time torque test. 

Perform the torque test and the additional 

torque procedures as stated in the 

Accomplishment Instructions, paragraph 

3.B.(1) through 3.B.(3) of the ASB. The torque 

test is not required at the recurring 

inspection intervals of the lower bifilar arm 

assembly. 

(b) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Boston Aircraft 

Certification Office, FAA, for information 

about previously approved alternative 

methods of compliance. 

(c) Inspect the lower bifilar arm assembly 

and perform the torque test by following the 

specified portions of Sikorsky Alert Service 

Bulletin No. 76–65–62, dated December 14, 

2004. The Director of the Federal Register 

approved this incorporation by reference in 

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

part 51. Copies may be obtained from 

Sikorsky Aircraft Corporation, Attn: Manager, 

Commercial Tech Support, 6900 Main Street, 

Stratford, Connecticut 06614, phone (203) 

386–3001, fax (203) 386–5983. Copies may be 

inspected 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. 

(d) This amendment becomes effective on 

November 10, 2005. 

Issued in Fort Worth, Texas, on October 17, 

2005. 

David A. Downey, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 05–21256 Filed 10–25–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22018; Directorate 

Identifier 2005–CE–41–AD; Amendment 39–

14348; AD 2005–22–04] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Models PC–12 and PC–12/ 

45 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for certain 

Pilatus Aircraft Ltd. (Pilatus) Models 

PC–12 and PC–12/45 airplanes. This AD 

requires you to determine (maintenance 

records check and/or inspection) 

whether certain nose landing gear 

(NLG), main landing gear (MLG), and 

MLG shock absorber assemblies with a 

serial number beginning with ‘‘AM’’ are 

61724 Federal Register / Vol. 70, No. 206 / Wednesday, October 26, 2005 / Rules and Regulations 

installed, and, if installed, would 

require you to replace them with ones 

without the ‘‘AM.’’ This AD is the result 

of mandatory continuing airworthiness 

information (MCAI) issued by the 

airworthiness authority for Switzerland. 

We are issuing this AD to detect and 

correct the NLG, MLG, and MLG shock 

absorber assemblies that are affected by 

hydrogen embrittlement, which could 

result in failure of the landing gear. This 

failure could lead to nose or main 

landing gear collapse during operation 

with consequent loss of airplane 

control. 

DATES: This AD becomes effective on 

December 12, 2005. 

As of December 12, 2005, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation. 

ADDRESSES: To get the service 

information identified in this AD, 

contact Pilatus Aircraft Ltd., Customer 

Liaison Manager, CH–6371 Stans, 

Switzerland; telephone: +41 41 619 

6208; facsimile: +41 41 619 7311; email: SupportPC12@pilatus-aircraft.com 

or from Pilatus Business Aircraft Ltd., 

Product Support Department, 11755 

Airport Way, Broomfield, Colorado 

80021; telephone: (303) 465–9099; 

facsimile: (303) 465–6040. 

To view the AD docket, go to the 

Docket Management Facility; U.S. 

Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

001 or on the Internet at http:// 

dms.dot.gov. The docket number is 

FAA–2005–22018; Directorate Identifier 

2005–CE–41–AD. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329–

4059; facsimile: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

What events have caused this AD? 

The Federal Office for Civil Aviation 

(FOCA), which is the airworthiness 

authority for Switzerland, recently 

notified FAA that an unsafe condition 

may exist on Pilatus Models PC–12 and 

PC–12/45 airplanes. The FOCA reports 

that some components of the main 

landing gear (MLG), nose landing gear 

(NLG), and MLG shock absorber 

assemblies have the potential to fail 

during operation. 

Investigations revealed that an 

improper cadmium plating process 

applied to the high strength steel part 

causes the problem. This can result in 

hydrogen embrittlement. Affected are 

only components that are installed on 

MLG, NLG, and MLG shock absorber 

assemblies, with serial numbers that 

start with the letters ‘‘AM.’’ Components 

in this condition can experience a 

decreased fatigue life. 

What is the potential impact if FAA 

took no action? Failure of the nose or 

main landing gear could lead to nose or 

main landing gear collapse during 

operation with consequent loss of 

airplane control. 

Has FAA taken any action to this 

point? We issued a proposal to amend 

part 39 of the Federal Aviation 

Regulations (14 CFR part 39) to include 

an AD that would apply to certain 

Pilatus Aircraft Ltd. (Pilatus) Models 

PC–12 and PC–12/45 airplanes. This 

proposal was published in the Federal 

Register as a notice of proposed 

rulemaking (NPRM) on August 22, 2005 

(70 FR 48914). The NPRM proposed to 

require you to determine (maintenance 

records check and/or inspection) 

whether certain nose landing gear 

(NLG), main landing gear (MLG), and 

MLG shock absorber assemblies with a 

serial number beginning with ‘‘AM’’ are 

installed, and, if installed, would 

require you to replace them with ones 

without the ‘‘AM.’’

Comments 

Was the public invited to comment? 

We provided the public the opportunity 

to participate in developing this AD. We 

received no comments on the proposal 

or on the determination of the cost to 

the public. 

Conclusion 

What is FAA’s final determination on 

this issue? We have carefully reviewed 

the available data and determined that 

air safety and the public interest require 

adopting the AD as proposed except for 

minor editorial corrections. We have 

determined that these minor 

corrections: 

—Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

—Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Changes to 14 CFR Part 39—Effect on 

the AD 

How does the revision to 14 CFR part 

39 affect this AD? On July 10, 2002, the 

FAA published a new version of 14 CFR 

part 39 (67 FR 47997, July 22, 2002), 

which governs the FAA’s AD system. 

This regulation now includes material 

that relates to altered products, special 

flight permits, and alternative methods 

of compliance. This material previously 

was included in each individual AD. 

Since this material is included in 14 

CFR part 39, we will not include it in 

future AD actions. 

Costs of Compliance 

How many airplanes does this AD 

impact? We estimate that this AD affects 

350 airplanes in the U.S. registry. 

What is the cost impact of this AD on 

owners/operators of the affected 

airplanes? We estimate the following 

costs to do the check of the logbook to 

identify NLG, MLG, and MLG shock 

absorber assemblies with serial numbers 

that start with the letters AM: 

Labor cost Parts cost Total cost per 

airplane 

Total cost on U.S. 

operators 

1 work hour × $65 per hour = $65 .................................................... Not applicable ............................. $65 350 × $65 = $22,750. 

We estimate the following costs to do 

any necessary inspection and 

replacement of all possible NLG, MLG, 

and MLG shock absorber assemblies that 

would be required based on the results 

of this check of the logbook. We have no 

way of determining the number of 

airplanes that may need this 

replacement: 

Labor cost Parts cost Total cost per airplane 

41 work hours × $65 per hour = $2,665 ............ $3,800 for the NLG kit, $850 for the MLG kit, 

and $2,600 for the MLG shock absorber assembly kit.

$2,665 + $3,800 + $850 + $2,600 = $9,915. 

Federal Register / Vol. 70, No. 206 / Wednesday, October 26, 2005 / Rules and Regulations 61725 

Pilatus will provide warranty credit 

for replacing the specified assemblies to 

the extent stated in the service 

information. 

Authority for This Rulemaking 

What authority does FAA have for 

issuing this rulemaking action? 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 AD. 

Regulatory Findings 

Will this AD impact various entities? 

We have 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. 

Will this AD involve a significant rule 

or regulatory action? 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 the 

DOT Regulatory Policies and Procedures 

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

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a summary of the costs 

to comply with this AD (and other 

information as included in the 

Regulatory Evaluation) and placed it in 

the AD Docket. You may get a copy of 

this summary by sending a request to us 

at the address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2005–22018; 

Directorate Identifier 2005–CE–41–AD’’

in your request. 

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 Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. FAA amends § 39.13 by adding a 

new AD to read as follows: 

2005–22–04 Pilatus Aircraft Ltd.: 

Amendment 39–14348; Docket No. 

FAA–2005–22018; Directorate Identifier 

2005–CE–41–AD. 

When Does This AD Become Effective? 

(a) This AD becomes effective on December 

12, 2005. 

What Other ADs Are Affected by This 

Action? 

(b) None. 

What Airplanes Are Affected by This AD? 

(c) This AD affects Models PC–12 and PC–

12/45 airplanes, manufacturer serial numbers 

(MSN) 101 through MSN 625, that are 

certificated in any category. 

What Is the Unsafe Condition Presented in 

This AD? 

(d) This AD is the result of mandatory 

continuing airworthiness information (MCAI) 

issued by the airworthiness authority for 

Switzerland. The actions specified in this AD 

are intended to detect and correct the nose 

landing gear (NLG), main landing gear 

(MLG), and MLG shock absorber assemblies 

that are affected by hydrogen embrittlement, 

which could result in failure of the landing 

gear. This failure could lead to nose or main 

landing gear collapse during operation with 

consequent loss of airplane control. 

What Must I Do To Address This Problem? 

(e) To address this problem, you must do 

the following: 

Actions Compliance Procedures 

(1) Maintenance Records Check: 

(i) For MSN 101 through MSN 471 and MSN 473 through MSN 482: 

Check the maintenance records to determine whether the following 

replacements have been made: 

(A) Nose landing gear (NLG) assemblies, part number (P/N) 

532.20.12.038 and P/N 532.20.12.039 with serial numbers (S/N) AM 

001 through AM 045 and AM 048 through AM 054; 

(B) Main landing gear (MLG) assemblies, P/N 532.10.12.049 and P/N 

532.10.12.050 with S/N AM 001 through AM 027, AM 029 through 

AM 045, AM 047 through AM 050, AM 052, and AM 053; and 

Within the next 100 hours time-inservice (TIS) or 12 calendar 

months after December 12, 

2005 (the effective date of this 

AD), whichever occurs first, unless already done..

No special procedures necessary 

to check the maintenance 

records. 

(C) MLG shock absorber assemblies, P/N 532.10.12.175, with S/N AM 

001 through AM 017, AM 019, AM 021 through AM 063, AM 065 

through AM 070, AM 072 through AM 074, AM 080, AM 084, AM 

086, AM 089, AM 090, AM 093 through AM 096, AM 099, AM 103 

through AM 107. 

...................................................

(ii) For MSN 472 and MSN 483 through MSN 625: Verify that the S/N 

parts identified in paragraphs (e)(1)(i)(A), (e)(1)(i)(B), and (e)(1)(i)(C) 

of this AD have not been installed. 

...................................................

(iii) The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 

CFR 43.7) may make this check. You must make an entry into the 

aircraft records that shows compliance with this portion of the AD in 

accordance with section 43.9 of the Federal Aviation Regulations 

(14 CFR 43.9). 

...................................................

61726 Federal Register / Vol. 70, No. 206 / Wednesday, October 26, 2005 / Rules and Regulations 

Actions Compliance Procedures 

(2) If you find as a result of the check required by paragraph (e)(1)(i) 

of this AD that there is no record of the specified assembly replacement, or as a result of the check required by paragraph (e)(1)(ii) of 

this AD that parts have been installed in service, then inspect: 

(i) The NLG assemblies, P/N 532.20.12.038 and P/N 532.20.12.039, 

for any S/N that starts with AM 001 through AM 045 and AM 048 

through AM 054. 

Within the next 100 hours time-inservice (TIS) or 12 calendar 

months after December 12, 

2005 (the effective date of this 

AD), whichever occurs first, unless already done..

Follow Pilatus PC12 Service Bulletin No. 32–016, dated March 

11, 2004. 

(ii) The MLG assemblies, P/N 532.10.12.049 and P/N 532.10.12.050, 

for any S/N that starts with AM 001 through AM 027, AM 029 

through AM 045, AM 047 through AM 050, AM 052, and AM 053. 

(iii) The MLG shock absorber assemblies, P/N 532.10.12.175, for any 

S/N that starts with AM 001 through AM 017, AM 019, AM 021 

through AM 063, AM 065 through AM 070, AM 072 through AM 

074, AM 080, AM 084, AM 086, AM 089, AM 090, AM 093 through 

AM 096, AM 099, and AM 103 through AM 107. 

(iv) You may choose to do the inspection without doing the maintenance records check. 

(3) If during the inspection required by paragraph (e)(2) of this AD, 

you find: 

(i) Any NLG assembly, P/N 532.20.12.038 and P/N 532.20.12.039, 

with any S/N that starts with AM 001 through AM 045 or AM 048 

through AM 054, replace the NLG specific components with new 

components. 

(ii) Any MLG assembly, P/N 532.10.12.049 and P/N 532.10.12.050, 

with any S/N that starts with AM 001 through AM 027, AM 029 

through AM 045, AM 047 through AM 050, AM 052, or AM 053, replace the MLG specific components with new components. 

Before further flight after the inspection required by paragraph 

(e)(2) of this AD.

Follow Pilatus PC12 Service Bulletin No. 32–016, dated March 

11, 2004. 

(iii) Any MLG shock absorber assembly, P/N 532.10.12.175, with any 

S/N that starts with AM 001 through AM 017, AM 019, AM 021 

through AM 063, AM 065 through AM 070, AM 072 through AM 

074, AM 080, AM 084, AM 086, AM 089, AM 090, AM 093 through 

AM 096, AM 099, or AM 103 through AM 107, replace the MLG 

shock absorber specific components with new components. 

(4) Do not install: 

(i) Any NLG assembly, P/N 532.20.12.038 and P/N 532.20.12.039, 

with any S/N that starts with AM 001 through AM 045 or AM 048 effective through AM 054. 

As of December 12, 2005 (the effective date of this AD) Not Applicable. 

(ii) Any MLG assembly, P/N 532.10.12.049 and P/N 532.10.12.050, 

with any S/N that starts with AM 001 through AM 027, AM 029 

through AM 045, AM 047 through AM 050, AM 052, or AM 053. 

(iii) Any MLG shock absorber assembly, P/N 532.10.12.175, with any 

S/N that starts with AM 001 through AM 017, AM 019, AM 021 

through AM 063, AM 065 through AM 070, AM 072 through AM 

074, AM 080, AM 084, AM 086, AM 089, AM 090, AM 093 through 

AM 096, AM 099, or AM 103 through AM 107. 

Note 1: AD 2002–14–22, issued on July 8, 

2002 (67 FR 46582), and AD 2004–06–05, 

issued on March 15, 2004 (69 FR 13712), are 

still applicable. 

Note 2: The FAA recommends that you 

send any removed parts or assemblies to 

Pilatus. 

May I Request an Alternative Method of 

Compliance? 

(f) You may request a different method of 

compliance or a different compliance time 

for this AD by following the procedures in 14 

CFR 39.19. Unless FAA authorizes otherwise, 

send your request to your principal 

inspector. The principal inspector may add 

comments and will send your request to the 

Manager, Standards Office, Small Airplane 

Directorate, FAA. For information on any 

already approved alternative methods of 

compliance, contact Doug Rudolph, 

Aerospace Engineer, FAA, Small Airplane 

Directorate, 901 Locust, Room 301, Kansas 

City, Missouri 64106; telephone: (816) 329–

4059; facsimile: (816) 329–4090. 

Is There Other Information That Relates to 

This Subject? 

(g) Swiss AD Number HB–2005–168, dated 

May 3, 2005, also addresses the subject of 

this AD. 

Does This AD Incorporate Any Material by 

Reference? 

(h) You must do the actions required by 

this AD following the instructions in Pilatus 

PC12 Service Bulletin No. 32–016, dated 

March 11, 2004. The Director of the Federal 

Register approved the incorporation by 

reference of this service bulletin in 

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

part 51. To get a copy of this service 

information, contact Pilatus Aircraft Ltd., 

Customer Liaison Manager, CH–6371 Stans, 

Switzerland; telephone: +41 41 619 6208; 

facsimile: +41 41 619 7311; e-mail: 

SupportPC12@pilatus-aircraft.com or from 

Pilatus Business Aircraft Ltd., Product 

Support Department, 11755 Airport Way, 

Broomfield, Colorado 80021; telephone: (303) 

465–9099; facsimile: (303) 465–6040. To 

review copies of this service information, go 

to the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, go 

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

code_of_federal_regulations/ 

ibr_locations.html or call (202) 741–6030. To 

view the AD docket, go to the Docket 

Management Facility; U.S. Department of 

Transportation, 400 Seventh Street, SW., 

Nassif Building, Room PL–401, Washington, 

DC 20590–001 or on the Internet at http:// 

dms.dot.gov. The docket number is FAA–

2005–22018; Directorate Identifier 2005–CE–

41–AD. 

Federal Register / Vol. 70, No. 206 / Wednesday, October 26, 2005 / Rules and Regulations 61727 

Issued in Kansas City, Missouri, on 

October 19, 2005. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–21255 Filed 10–25–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20692; Directorate 

Identifier 2004–NM–229–AD; Amendment 

39–14350; AD 2005–22–06] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747SR, and 747SP Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 747–100, 747–100B, 747–

100B SUD, 747–200B, 747–200C, 747–

200F, 747–300, 747SR, and 747SP series 

airplanes. This AD requires doing a onetime high-frequency eddy current 

inspection and repetitive detailed 

inspections for cracks in the frame web 

of main entry door number 1; and 

repairing the door frame web if 

necessary. This AD also provides for 

optional terminating action for the 

repetitive inspections. This AD is 

prompted by reports of cracking at the 

upper aft corner of the cutout for main 

entry door number 1 in the station 488 

frame web. We are issuing this AD to 

detect and correct cracks in the frame 

web. These cracks could cause the frame 

to break and lead to rapid 

decompression of the airplane. 

DATES: This AD becomes effective 

November 30, 2005. 

The incorporation by reference of a 

certain publication listed in the AD is 

approved by the Director of the Federal 

Register as of November 30, 2005. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

Docket: The AD docket contains the 

proposed AD, comments, and any final 

disposition. You can examine the AD 

docket on the Internet at http:// 

dms.dot.gov, or in person at the Docket 

Management Facility office between 9 

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

Friday, except Federal holidays. The 

Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the U.S. Department of Transportation, 

400 Seventh Street SW., room PL–401, 

Washington, DC. This docket number is 

FAA–2005–20692; the directorate 

identifier for this docket is 2004–NM–

229–AD. 

FOR FURTHER INFORMATION CONTACT: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 917–6437; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

an AD for certain Boeing Model 747–

100, 747–100B, 747–100B SUD, 747–

200B, 747–200C, 747–200F, 747–300, 

747SR, and 747SP series airplanes. That 

action, published in the Federal 

Register on March 23, 2005 (70 FR 

14589), proposed to require doing a onetime high-frequency eddy current 

inspection and repetitive detailed 

inspections for cracks in the frame web 

of main entry door number 1; and 

repairing the door frame web if 

necessary. That action also proposed to 

provide for optional terminating action 

for the repetitive inspections. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been submitted on the proposed AD. 

Request To Include Optional Inspection 

One commenter requests that we 

include an option for Group 3 airplanes 

in paragraph (f) of the proposed AD to 

perform an open-hole high-frequency 

eddy current (HFEC) inspection every 

3,000 flight cycles instead of a detailed 

inspection every 1,500 flight cycles. The 

commenter states that the manufacturer 

has found this optional inspection to be 

structurally acceptable. 

We agree with the commenter that 

performing an HFEC inspection every 

3,000 flight cycles would provide an 

equivalent level of safety as intended by 

this AD. However, the repetitive 

detailed inspection requirement is 

actually specified in paragraph (g) of the 

proposed AD, not paragraph (f). 

Therefore, we have revised paragraph 

(g) of the final rule, for Group 3 

airplanes only, to include an option to 

perform a surface HFEC inspection of 

the frame web between the upper door 

sill and door stop number 8 for cracks 

every 3,000 flight cycles in accordance 

with the method referenced in Figure 3 

or Figure 4 of the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin (ASB) 747–53A2508, dated 

August 19, 2004. 

Request To Revise Frame Inner Chord 

Inspection Requirement 

One commenter requests that we 

delete paragraph (j) of the proposed AD 

or revise it to state that when the frame 

inner chord is being replaced 

concurrently with the required frame 

web repairs, the open-hole HFEC 

inspection of the frame inner chord is 

not required. The commenter states that 

the intent of paragraph (j) should be that 

when the frame inner chord is being 

replaced, there is no need to inspect the 

existing fastener holes in the chord 

because the chord is a new part. The 

commenter refers to the applicable 

Boeing Structural Repair Manual (SRM) 

and Boeing ASB 747–53A2508 to 

support this contention. 

We agree with this request. Open-hole 

HFEC inspection of the frame inner 

chord is a conditional inspection 

included in the repair procedures 

specified in paragraph (h) of this AD. 

However, AD 91–11–01, amendment 

39–6997 (dated May 15, 1991), 

referenced in paragraph (j) of the 

proposed AD, only requires inspecting 

the frame inner chord, while AD 90–06–

06, amendment 39–6490 (dated March 

7, 1990), actually requires replacing the 

frame inner chord. Therefore, we have 

concluded that paragraph (j) of the 

proposed AD should have referred to 

AD 90–06–06, rather than AD 91–11–01, 

regarding concurrent replacement of the 

frame inner chord. We have revised 

paragraph (j) of the final rule to reflect 

the commenter’s request and to 

correctly refer to AD 90–06–06. Further, 

to ensure that there is no confusion 

about the HFEC inspection, we also 

revised paragraph (h) of the final rule to 

include a reference to an ‘‘open-hole’’

HFEC inspection. 

Request To Clarify Use of Structural 

Repair Manual 

The same commenter requests that 

paragraph (h) of the proposed AD be 

clarified. The commenter asserts that 

paragraph (h) should be revised to state 

that the Boeing SRM meets the intent of 

the proposed AD. Further, the 

commenter requests that we clarify the 

statement ‘‘For a repair method to be 

approved, the approval must 

specifically reference this AD.’’ The 

commenter feels that paragraph (h) as 

written might lead to confusion. 

We agree with the commenter that the 

Boeing SRM procedures specified in the