54616 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Rules and Regulations 

Boeing Alert Service Bulletin 747–54A2218, 

dated June 17, 2004, are considered 

acceptable for compliance with the 

corresponding actions specified in paragraph 

(f) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Seattle ACO, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

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. 

Material Incorporated by Reference 

(k) You must use Boeing Service Bulletin 

747–54A2218, Revision 1, dated February 24, 

2005, to perform the actions that are required 

by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approves the incorporation by 

reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. To 

get copies of the service information, contact 

Boeing Commercial Airplanes, P.O. Box 

3707, Seattle, Washington 98124–2207. To 

view the AD docket, go to the Docket 

Management Facility, U.S. Department of 

Transportation, 400 Seventh Street SW., 

room PL–401, Nassif Building, Washington, 

DC. To review copies of the service 

information, go to the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the 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 

September 8, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–18313 Filed 9–15–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21140; Directorate 

Identifier 2004–NM–274–AD; Amendment 

39–14273; AD 2005–19–08] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Model DC–9–14, DC–9–15, 

and DC–9–15F Airplanes; and 

McDonnell Douglas Model DC–9–20, 

DC–9–30, DC–9–40, and DC–9–50 

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 all 

transport category airplanes listed 

above. This AD requires repetitive 

inspections for cracks of the main 

landing gear (MLG) shock strut cylinder, 

and related investigative and corrective 

actions if necessary. This AD results 

from two reports of a collapsed MLG 

and a report of cracks in two MLG 

cylinders. We are issuing this AD to 

detect and correct fatigue cracks in the 

shock strut cylinder of the MLG, which 

could result in a collapsed MLG during 

takeoff or landing, and possible reduced 

structural integrity of the airplane. 

DATES: This AD becomes effective 

October 21, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 21, 2005. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., Nassif Building, room PL–401, 

Washington, DC. 

Contact Boeing Commercial 

Airplanes, Long Beach Division, 3855 

Lakewood Boulevard, Long Beach, 

California 90846, Attention: Data and 

Service Management, Dept. C1–L5A 

(D800–0024), for service information 

identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Wahib Mina, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; telephone (562) 

627–5324; fax (562) 627–5210. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (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 street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to all McDonnell Douglas Model 

DC–9–14, DC–9–15, and DC–9–15F 

airplanes; Model DC–9–21 airplanes; 

Model DC–9–31, DC–9–32, DC–9–32 

(VC–9C), DC–9–32F, DC–9–33F, DC–9–

34, DC–9–34F, and DC–9–32F (C–9A, 

C–9B) airplanes; Model DC–9–41 

airplanes; and Model DC–9–51 

airplanes. That NPRM was published in 

the Federal Register on May 9, 2005 (70 

FR 24338). That NPRM proposed to 

require repetitive inspections for cracks 

of the main landing gear (MLG) shock 

strut cylinder, and related investigative 

and corrective actions if necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Request to Refer to Latest Service 

Bulletin Revision 

The commenter, an airplane operator, 

states that the manufacturer is planning 

to revise Boeing Alert Service Bulletin 

DC9–32A350, dated December 3, 2004, 

which was cited as the appropriate 

source of service information for the 

action in the NPRM. The commenter 

asks that we revise paragraph (f) to refer 

to the new revision of the service 

bulletin, and that we also give credit for 

the actions done in accordance with the 

original issue of the service bulletin. In 

addition, the commenter requests that 

we address certain references in the 

service bulletin that are incorrect. 

We agree with the commenter. We 

have revised paragraph (f) of the final 

rule to refer to Boeing Alert Service 

Bulletin DC9–32A350, Revision 1, dated 

August 3, 2005, as the appropriate 

source of service information. We have 

also added a new paragraph (l) to give 

credit for the actions done in 

accordance with the original issue of the 

service bulletin, and re-identified the 

subsequent paragraph accordingly. 

Revision 1 of the service bulletin does 

not increase the scope of the AD; 

Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Rules and Regulations 54617 

however it corrects certain references, 

including incorrect references to certain 

procedures for paint removal from the 

inspection area. 

Request to Add Optional Terminating 

Action 

The same commenter states that the 

manufacturer has designed a newmaterial shock strut cylinder that is not 

air-melted. The commenter states that 

installing this new part should be 

considered as an optional terminating 

action for the inspections in the NPRM. 

The commenter points out that 

cylinders that are not air-melted are not 

subject to the unsafe condition 

addressed in the NPRM. 

We disagree with the commenter. The 

manufacturer has advised us it has 

designed a new-material shock strut 

cylinder that is not air-melted, although 

this part is not yet available. However, 

operators may request alternative 

methods of compliance with the 

requirements of this rule; paragraph (n) 

of the final rule includes a provision for 

the approval of such methods. We have 

not changed the final rule in this regard. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

There are about 644 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. 

ESTIMATED COSTS

Action Work 

hours 

Average 

labor rate 

per hour 

Parts Cost per 

airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection, per inspection 

cycle.

4 to 6 ........... $65 None ................. $260 to $390 426 $110,760 to $166,140, per inspection cycle. 

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 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 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. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2005–19–08 McDonnell Douglas: 

Amendment 39–14273. Docket No. 

FAA–2005–21140; Directorate Identifier 

2004–NM–274–AD. 

Effective Date 

(a) This AD becomes effective October 21, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all McDonnell 

Douglas Model DC–9–14, DC–9–15, and DC–

9–15F airplanes; Model DC–9–21 airplanes; 

Model DC–9–31, DC–9–32, DC–9–32 (VC–

9C), DC–9–32F, DC–9–33F, DC–9–34, DC–9–

34F, and DC–9–32F (C–9A, C–9B) airplanes; 

Model DC–9–41 airplanes; and Model DC–9–

51 airplanes; certificated in any category. 

Unsafe Condition 

(d) This AD results from two reports of a 

collapsed main landing gear (MLG) and a 

report of cracks in two MLG cylinders. We 

are issuing this AD to detect and correct 

fatigue cracks in the shock strut cylinder of 

the MLG, which could result in a collapsed 

MLG during takeoff or landing, and possible 

reduced structural integrity of the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Service Bulletin Reference Paragraph 

(f) The term ‘‘service bulletin,’’ as used in 

this AD, means the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

DC9–32A350, Revision 1, dated August 3, 

2005. 

Records Review 

(g) Before the applicable compliance time 

specified in paragraph (h) or Table 1 of this 

AD, as applicable, do the applicable actions 

in paragraphs (g)(1) and (g)(2) of this AD. 

(1) For all airplane groups: Review the 

airplane maintenance records of the MLG to 

54618 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Rules and Regulations 

determine its service history and the number 

of landings on the MLG shock strut cylinder. 

(2) For Group 3 airplanes identified in the 

service bulletin: Review the maintenance 

records to determine if the MLG cylinder on 

each Group 3 airplane has always been on a 

Group 3 airplane, and do the actions in 

paragraph (k) of this AD. 

Inspection 

(h) Inspect the MLG shock strut cylinders 

for cracks using the Option 1 or Option 2 

non-destructive testing inspection described 

in the service bulletin. Inspect in accordance 

with the Accomplishment Instructions of the 

service bulletin. Do the detailed inspection 

before the accumulation of 60,000 total 

landings on the MLG, or at the applicable 

grace period specified in Table 1 of this AD, 

whichever occurs later, except as provided 

by paragraph (k) of this AD. If the review of 

maintenance records is not sufficient to 

conclusively determine the service history 

and number of landings on the MLG shock 

strut cylinder, perform the initial inspection 

at the applicable grace period specified in 

Table 1 of this AD. 

TABLE 1.—GRACE PERIOD AND REPETITIVE INTERVAL

Airplanes identified in the service bulletin as 

group Grace period Repetitive interval 

1 ......................................................................... Within 18 months or 650 landings after the effective date of this AD, whichever occurs 

first.

Intervals not to exceed 650 landings. 

2 ......................................................................... Within 18 months or 500 landings after the effective date of this AD, whichever occurs 

first.

Intervals not to exceed 500 landings. 

3, except as provided by paragraph (k) of this 

AD.

Within 18 months or 2,500 landings after the 

effective date of this AD, whichever occurs 

first.

Intervals not to exceed 2,500 landings. 

4 ......................................................................... Within 18 months or 2,100 landings after the 

effective date of this AD, whichever occurs 

first.

Intervals not exceed 2,100 landings. 

No Crack Indication Found 

(i) If no crack indication is found during 

the inspection required by paragraph (h) of 

this AD, repeat the inspection at the 

applicable interval specified in Table 1 of 

this AD. 

Related Investigative and Corrective Actions 

(j) If any crack indication is found during 

any inspection required by paragraph (h) or 

(i) of this AD, before further flight: Confirm 

the crack indication by doing all applicable 

related investigative actions and doing the 

applicable corrective actions in accordance 

with the service bulletin. Repeat the 

inspection at the applicable threshold and 

interval specified in paragraph (h) of this AD. 

MLG Cylinder Previously Installed on Group 

4 Airplanes 

(k) For MLG cylinders on Group 3 

airplanes as identified in the service bulletin: 

If the MLG cylinder was previously installed 

on a Group 4 airplane, as identified in the 

service bulletin, or if the service history and 

number of landings cannot be determined, 

the MLG cylinder must be inspected at the 

grace period and repetitive interval that 

applies to Group 4 airplanes, as specified in 

Table 1 of this AD. 

Actions Accomplished in Accordance With 

Original Issue of Service Bulletin 

(l) Actions done before the effective date of 

this AD in accordance with Boeing Alert 

Service Bulletin DC9–32A350, dated 

December 3, 2004, are acceptable for 

compliance with the corresponding actions 

required by this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(m) The Manager, Los Angeles Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

Material Incorporated by Reference 

(n) You must use Boeing Alert Service 

Bulletin DC9–32A350, Revision 1, dated 

August 3, 2005, to perform the actions that 

are required by this AD, unless the AD 

specifies otherwise. The Director of the 

Federal Register approved the incorporation 

by reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Boeing Commercial Airplanes, Long 

Beach Division, 3855 Lakewood Boulevard, 

Long Beach, California 90846, Attention: 

Data and Service Management, Dept. C1–L5A 

(D800–0024), for a copy of this service 

information. You may review copies at the 

Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street SW., room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the NARA, call (202) 741–6030, 

or go to http://www.archives.gov/federalregister/cfr/ibr-locations.html. 

Issued in Renton, Washington, on 

September 7, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–18314 Filed 9–15–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21864; Directorate 

Identifier 2005–NE–29–AD; Amendment 39–

14276; AD 2005–19–11] 

RIN 2120–AA64 

Airworthiness Directives; Lycoming 

Engines (Formerly Textron Lycoming) 

AEIO–360, IO–360, O–360, LIO–360, 

LO–360, AEIO–540, IO–540, O–540, and 

TIO–540 Series Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Lycoming Engines (formerly Textron 

Lycoming) AEIO–360, IO–360, O–360, 

LIO–360, LO–360, AEIO–540, IO–540, 

O–540, and TIO–540 series 

reciprocating engines rated at 300 

horsepower (HP) or lower. This AD 

requires replacing certain crankshafts. 

This AD results from reports of 12 

crankshaft failures in Lycoming 360 and 

540 series engines rated at 300 HP or 

lower. We are issuing this AD to prevent 

failure of the crankshaft, which could 

result in total engine power loss, inflight engine failure, and possible loss of 

the aircraft. 

DATES: This AD becomes effective 

October 21, 2005. The Director of the 

Federal Register approved the 

incorporation by reference of certain