Federal Register / Vol. 69, No. 46 / Tuesday, March 9, 2004 / Rules and Regulations 10917

the Manager, Los Angeles ACO, as required 

by this paragraph, the Manager’s approval 

letter must specifically refer to this AD. 

New Requirements of This AD 

No Requirement to Submit Information 

(d) Although Boeing Service Bulletin 

MD90–32–012, Revision 03, dated June 29, 

2001, specifies to submit information to the 

manufacturer, this AD does not include such 

a requirement. 

Clarification of Inspection Sequence 

(e) For inspections accomplished after the 

effective date of this AD: Where this AD 

requires fluorescent penetrant and magnetic 

particle inspections, accomplishment of the 

fluorescent penetrant inspection must 

precede accomplishment of the magnetic 

particle inspection. 

Inspection of MLG Piston P/Ns 5935347–1 

through –509, –511, and –513; and 

SR09320081–3 through –13

(f) For any MLG piston having P/N 

5935347–1 through –509, –511, or –513; or P/

Ns SR09320081–3 through –13: Perform 

fluorescent penetrant and magnetic particle 

inspections to detect fatigue cracking of the 

MLG pistons, in accordance with Boeing 

Service Bulletin MD90–32–012, Revision 03, 

dated June 29, 2001. Do the initial 

inspections at the later of the times specified 

in paragraphs (f)(1) and (f)(2) of this AD, 

except as provided by paragraph (g) of this 

AD. Repeat the inspections thereafter at 

intervals not to exceed 5,000 landings.

(1) Prior to the accumulation of 4,000 total 

landings; or 

(2) Within 2,500 landings or 12 months 

after the effective date of this AD, whichever 

is first. 

MLG Pistons Inspected Per Paragraph (a) or 

(b) of This AD 

(g) MLG pistons having P/N 5935347–509, 

–511, or –513 that have been inspected as 

required by paragraph (a) or (b) of this AD, 

as applicable, are not required to be 

reinspected per paragraph (f) of this AD. 

Repetitive Inspections for Evidence of 

Cracking and Follow-on Actions 

(h) During the first brake change after the 

effective date of this AD, perform a general 

visual inspection to find evidence of cracking 

in the paint topcoat of the MLG piston, per 

the Accomplishment Instructions of Boeing 

Service Bulletin MD90–32–012, Revision 03, 

dated June 29, 2001. Repeat this inspection 

during every brake change. 

(1) If any evidence of cracking in the paint 

topcoat, as described in the service bulletin, 

is found: Within 7 days or 50 landings after 

the evidence is found, whichever is first, 

perform a non-destructive test (NDT) 

inspection of the MLG piston to determine if 

there is any cracking. 

(2) If any crack is found during the NDT 

inspection required by paragraph (h)(1) of 

this AD, before further flight, repair per a 

method approved by the Manager, Los 

Angeles ACO. For a repair method to be 

approved by the Manager, Los Angeles ACO, 

as required by this paragraph, the Manager’s 

approval letter must specifically refer to this 

AD.

Note 1: For the purposes of this AD, a 

general visual inspection is defined as: ‘‘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 enhance visual 

access to all exposed 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.’’

Inspections Accomplished Per Previous 

Issue of Service Bulletin 

(i) Inspections accomplished before the 

effective date of this AD per McDonnell 

Douglas Service Bulletin MD90–32–012, 

Revision 02, dated June 29, 1999, are 

considered acceptable for compliance with 

the corresponding actions specified in this 

AD. 

Replacement of MLG Shock Strut Piston 

Assemblies 

(j) Before the accumulation of 30,000 total 

landings on the MLG shock strut piston 

assemblies, or within 5,000 landings after 

June 20, 2002 (the effective date of AD 2002–

10–03, amendment 39–12749), whichever 

occurs later: Replace the MLG shock strut 

piston assemblies, left- and right-hand sides, 

with new or serviceable improved 

assemblies, per the Accomplishment 

Instructions of Boeing Service Bulletin 

MD90–32–031, Revision 01, dated April 25, 

2001. If the MLG shock strut piston is not 

serialized or the number of landings on the 

piston cannot be conclusively determined, 

consider the total number of landings on the 

piston assembly to be equal to the total 

number of landings accumulated by the 

airplane with the highest total number of 

landings in the operator’s fleet.

Note 2: Paragraph (a) of AD 2002–10–03, 

amendment 39–12749, requires the same 

actions as paragraph (j) of this AD.

Compliance With Requirements of Other 

ADs 

(k) Accomplishment of the replacement 

required by paragraph (j) of this AD 

constitutes terminating action for the 

requirements of this AD and AD 2002–10–03, 

amendment 39–12749, for the Model MD–

90–30 airplanes listed in Boeing Service 

Bulletin MD90–32–012, Revision 03, dated 

June 29, 2001. 

Alternative Methods of Compliance 

(l)(1) In accordance with 14 CFR 39.19, the 

Manager, Los Angeles ACO, is authorized to 

approve alternative methods of compliance 

for this AD. 

(2) Alternative methods of compliance, 

approved previously per AD 2000–03–08, 

amendment 39–11567, are approved as 

alternative methods of compliance with 

paragraphs (a), (b), and (c) of this AD. 

Incorporation by Reference 

(m) Unless otherwise specified in this AD, 

the actions must be done in accordance with 

McDonnell Douglas Service Bulletin MD90–

32–012, dated May 19, 1997, or McDonnell 

Douglas Service Bulletin MD90–32–012, 

Revision 01, dated June 2, 1998; Boeing 

Service Bulletin MD90–32–012, Revision 03, 

dated June 29, 2001; and Boeing Service 

Bulletin MD90–32–031, Revision 01, dated 

April 25, 2001; as applicable. 

(1) The incorporation by reference of 

Boeing Service Bulletin MD90–32–012, 

Revision 03, dated June 29, 2001, is approved 

by the Director of the Federal Register in 

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

part 51. 

(2) The incorporation by reference of 

Boeing Service Bulletin MD90–32–031, 

Revision 01, dated April 25, 2001, was 

approved previously by the Director of the 

Federal Register as of June 20, 2002 (67 FR 

34823, May 16, 2002). 

(3) The incorporation by reference of 

McDonnell Douglas Service Bulletin MD90–

32–012, dated May 19, 1997; and McDonnell 

Douglas Service Bulletin MD90–32–012, 

Revision 01, dated June 2, 1998; was 

approved previously by the Director of the 

Federal Register as of March 22, 2000 (65 FR 

7719, February 16, 2000). 

(4) Copies may be obtained from Boeing 

Commercial Airplanes, Long Beach Division, 

3855 Lakewood Boulevard, Long Beach, 

California 90846, Attention: Data and Service 

Management, Dept. C1–L5A (D800–0024). 

Copies may be inspected at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or at the 

FAA, Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, California; or at the Office of the 

Federal Register, 800 North Capitol Street, 

NW., suite 700, Washington, DC. 

Effective Date 

(n) This amendment becomes effective on 

April 13, 2004.

Issued in Renton, Washington, on February 

25, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–4923 Filed 3–8–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2003–NM–49–AD; Amendment 

39–13511; AD 2004–05–16] 

RIN 2120–AA64

Airworthiness Directives; Boeing 

Model 767–200 and –300 Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

10918 Federal Register / Vol. 69, No. 46 / Tuesday, March 9, 2004 / Rules and Regulations 

applicable to certain Boeing Model 767–

200 and –300 series airplanes, that 

requires repetitive inspections of the aft 

pressure bulkhead web, and corrective 

action, if necessary. This action is 

necessary to detect and correct fatigue 

cracks in the aft pressure bulkhead web, 

which could result in uncontrolled 

rapid decompression. This action is 

intended to address the identified 

unsafe condition.

DATES: Effective April 13, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of April 13, 

2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Boeing Commercial Airplanes, 

P.O. Box 3707, Seattle, Washington 

98124–2207. This information may be 

examined at the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, Rules Docket, 

1601 Lind Avenue, SW., Renton, 

Washington; or at the Office of the 

Federal Register, 800 North Capitol 

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Suzanne Masterson, Airframe Branch, 

ANM–120S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056; 

telephone (425) 917–6441; fax (425) 

917–6590.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an airworthiness directive (AD) 

that is applicable to all Boeing Model 

767–200, –300, and –300F series 

airplanes was published in the Federal 

Register on October 6, 2003 (68 FR 

57639). That action proposed to require 

repetitive inspections of the aft pressure 

bulkhead web, and corrective action, if 

necessary. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

comments received. 

Concur With Proposed AD 

One commenter has reviewed the 

proposed AD and concurs with the 

proposed inspections and corrective 

action. 

Add Provision for Flight Cycles With 

Cabin Differential Pressure Less Than 

2.0 psi 

One commenter requests that a 

provision be added allowing flight 

cycles to not be counted if cabin 

differential pressure was below 2.0 

pounds per square inch (psi), provided 

that cabin pressure records be 

maintained for each airplane, and that 

no fleet averaging of cabin pressure is 

allowed. The commenter notes that 

there is a provision in Boeing Alert 

Service Bulletin 767–53A0087, dated 

October 21, 1999, which is the source of 

service information for this AD. In the 

‘‘General Notes’’ of the Accomplishment 

Instructions of the service bulletin, 

paragraph 6. specifies that ‘‘flightcycles, as defined herein, need not be 

counted if cabin differential pressure 

was below 2.0 psi.’’

We do not agree with the commenter’s 

request to add a provision for flight 

cycles with cabin differential pressure 

less than 2.0 psi. Cabin differential 

pressure of 2.0 psi or less is not typical 

of normal operation of the affected 

airplanes. We do not consider it 

appropriate to include various 

provisions in an AD applicable to 

unique uses of an affected airplane. We 

have determined that mitigating factors, 

such as total number of low pressure 

cycles, could best be evaluated through 

requests for alternative methods of 

compliance, as provided by paragraph 

(e) of this AD. In addition, we have 

clarified paragraphs (a) and (b) of this 

AD by referring to the ‘‘Work 

Instructions’’ of the service bulletin 

instead of the ‘‘Accomplishment 

Instructions.’’

Change Effectivity and Revise Affected 

Models 

One commenter requests the 

applicability be changed to line 

numbers 1 through 423 inclusive and 

that Model –300F series airplanes be 

removed from the list of affected 

models. The commenter states that AD 

2003–18–10, amendment 39–13301 (68 

FR 53503, September 11, 2003), 

mandates the current revision of Section 

9 of the Maintenance Planning Data 

document, which contains inspection 

item number 53–80–I01A. Inspection 

item number 53–80–I01A is the same as 

the proposed actions for line numbers 

424 and on. This would cause duplicate 

requirements for the same actions, 

causing confusion for operators as to 

what inspections to accomplish and 

how to comply with both ADs. 

The FAA agrees with the commenter’s 

request. For line numbers 424 and on, 

the Airworthiness Limitations for 

Boeing Model 767 series airplanes are 

currently in effect and AD 2003–18–10 

adequately mandates the proposed 

inspections and corrective action. We 

have changed the applicability to line 

numbers 1 through 423 inclusive and 

removed Model –300F series airplanes 

from the list of affected models. Because 

of the new applicability, we also 

removed Group 3 and Group 4 from 

Table 1 of this AD, revised paragraph (b) 

of this AD, and changed the number of 

affected airplanes in the ‘‘Cost Impact’’

paragraph of the AD.

Conclusion 

After careful review of the available 

data, including the comments noted 

above, the FAA has determined that air 

safety and the public interest require the 

adoption of the rule with the changes 

previously described. The FAA has 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Cost Impact 

There are approximately 406 

airplanes of the affected design in the 

worldwide fleet. The FAA estimates that 

182 airplanes of U.S. registry will be 

affected by this AD, that it will take 

approximately 14 work hours per 

airplane to accomplish the required 

inspection, and that the average labor 

rate is $65 per work hour. Based on 

these figures, the cost impact of the AD 

on U.S. operators is estimated to be 

$165,620, or $910 per airplane. 

The cost impact figure discussed 

above is based on assumptions that no 

operator has yet accomplished any of 

the requirements of this AD action, and 

that no operator would accomplish 

those actions in the future if this AD 

were not adopted. The cost impact 

figures discussed in AD rulemaking 

actions represent only the time 

necessary to perform the specific actions 

actually required by the AD. These 

figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Regulatory Impact 

The regulations adopted herein 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. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (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 

Federal Register / Vol. 69, No. 46 / Tuesday, March 9, 2004 / Rules and Regulations 10919

impact, positive or negative, on a 

substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES.

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 

the following new airworthiness 

directive:

2004–05–16 Boeing: Amendment 39–13511. 

Docket 2003–NM–49–AD.

Applicability: Model 767–200 and –300 

series airplanes, line numbers 1 through 423 

inclusive; certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To detect and correct fatigue cracks in the 

aft pressure bulkhead web, which could 

result in uncontrolled rapid decompression, 

accomplish the following:

Initial and Repetitive Inspections 

(a) Do high frequency eddy current 

inspections of the aft pressure bulkhead web, 

per the Work Instructions of Boeing Alert 

Service Bulletin 767–53A0087, dated October 

21, 1999; at the later of the applicable 

‘‘Threshold’’ and ‘‘Grace Period’’ times 

specified in Table 1 of this AD. Table 1 is as 

follows:

TABLE 1.—COMPLIANCE TIMES FOR INSPECTION

For— 

Compliance times— 

Threshold— Grace period— 

(1) Group 1 airplanes as identified in the 

service bulletin.

Prior to the accumulation of 37,500 

total flight cycles.

Within 18 months or within 3,000 flights after the effective 

date of this AD, whichever comes first 

(2) Group 2 airplanes as identified in the 

service bulletin.

Prior to the accumulation of 50,000 

total flight cycles.

Within 18 months or within 3,000 flights after the effective 

date of this AD, whichever comes first 

(b) If no crack is found during any 

inspection required by paragraph (a) of this 

AD, repeat the high frequency eddy current 

inspections thereafter at intervals not to 

exceed 6,000 flight cycles, per the Work 

Instructions of Boeing Alert Service Bulletin 

767–53A0087, dated October 21, 1999. 

Corrective Actions 

(c) If any crack is found during any 

inspection required by paragraph (a) or (b) of 

this AD and Boeing Alert Service Bulletin 

767–53A0087, dated October 21, 1999, 

specifies to contact Boeing for repair: Before 

further flight, repair per a method approved 

by the Manager, Seattle Aircraft Certification 

Office (ACO), FAA; or per data meeting the 

type certification basis of the airplane 

approved by a Boeing Company Designated 

Engineering Representative who has been 

authorized by the Manager, Seattle ACO, to 

make such findings. For a repair method to 

be approved, the approval must specifically 

reference this AD. 

Previously Installed Repairs 

(d) If previously installed repairs are 

installed in the inspection area, and Boeing 

Alert Service Bulletin 767–53A0087, dated 

October 21, 1999, specifies to contact Boeing 

for inspection details, an alternative method 

of compliance must be approved as required 

by sections 39.15, 39.17, and 39.19 of the 

Code of Federal Regulations (14 CFR 39.15, 

39.17, 39.19). 

Alternative Methods of Compliance 

(e) In accordance with 14 CFR 39.19, the 

Manager, Seattle ACO, FAA, is authorized to 

approve alternative methods of compliance 

for this AD. 

Incorporation by Reference 

(f) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Boeing Alert Service Bulletin 767–53A0087, 

dated October 21, 1999. This incorporation 

by reference was approved by the Director of 

the Federal Register in accordance with 5 

U.S.C. 552(a) and 1 CFR part 51. Copies may 

be obtained from Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207. Copies may be 

inspected at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or at the Office of the Federal 

Register, 800 North Capitol Street, NW., suite 

700, Washington, DC. 

Effective Date 

(g) This amendment becomes effective on 

April 13, 2004.

Issued in Renton, Washington, on February 

25, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–4922 Filed 3–8–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–04–AD; Amendment 

39–13491; AD 2004–04–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B2 and A300 B4 Series Airplanes; 

A300 B4–600, B4–600R, C4–605R 

Variant F, and F4–600R (Collectively 

Called A300–600); and A310 Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to all Airbus Model A300 B2 

and A300 B4 series airplanes; A300 B4–

600, B4–600R, C4–605R Variant F, and 

F4–600R (collectively called A300–600); 

and A310 series airplanes. This AD 

requires, for certain airplanes, 

identifying the part number of the 

landing gear selector valves. For all 

airplanes, this AD requires repetitive 

maintenance tasks or operational tests of 

the landing gear selector valves, and 

replacing discrepant valves with certain 

new valves. This action is necessary to 

prevent failure of the landing gear 

selector valves, which could result in 

residual pressure on the retraction 

chamber side of the electro-hydraulic