Federal Register / Vol. 67, No. 100 / Thursday, May 23, 2002 / Rules and Regulations 36085

(3) Copies may be obtained from Boeing 

Commercial Airplane Group, 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 

(k) This amendment becomes effective on 

June 27, 2002.

Issued in Renton, Washington, on May 14, 

2002. 

Vi L. Lipski, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 02–12635 Filed 5–22–02; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2000–NM–359–AD; Amendment 

39–12757; AD 2002–10–11] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–100, –200, –200C, –300, 

–400, and –500 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to certain Boeing Model 737 

series airplanes, that currently requires 

repetitive inspections for cracking and 

corrosion of the pressure bulkhead at 

body station (BS) 1016, and follow-on 

actions. This amendment expands the 

applicability of the existing AD, and 

requires new repetitive inspections to 

detect cracking and corrosion of the aft 

pressure bulkhead at BS 1016, and 

follow-on actions. This action is 

necessary to detect and correct 

corrosion or cracking of the aft pressure 

bulkhead at BS 1016, which could result 

in loss of the aft pressure bulkhead web 

and stiffeners and consequent rapid 

decompression of the fuselage. This 

action is intended to address the 

identified unsafe condition.

DATES: Effective June 27, 2002. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of June 27, 

2002.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Boeing Commercial Airplane 

Group, 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:

Scott Fung, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 227–1221; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 84–20–03 R1, 

amendment 39–5183 (50 FR 51235, 

December 16, 1985), which is applicable 

to certain Boeing Model 737 series 

airplanes, was published in the Federal 

Register on November 19, 2001 (66 FR 

57908). The action proposed to expand 

the applicability of the existing AD and 

require new repetitive inspections to 

detect cracking and corrosion of the aft 

pressure bulkhead at body station 1016, 

and follow-on actions. 

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. One commenter has 

no objection to the proposed rule. One 

commenter agrees with the intent of the 

proposed rule. 

Extend Compliance Time 

One commenter asks that the 

compliance time specified in paragraph 

(e)(3) of the proposed rule be extended 

by adding the following, ‘‘Do the 

inspection within 6 years since 

airplane’s date of manufacture, or 

within 4 years after doing tasks C53–

701–01.01 and C53–202–01 (reference 

Boeing Documents D6–38528 or D6–

38278), or within 2 years after the 

effective date of this AD, whichever 

occurs later.’’ The compliance time in 

paragraph (e)(3) now specifies, ‘‘Do the 

inspection within 6 years since the 

airplane’s date of manufacture, or 

within 2 years after the effective date of 

this AD, whichever occurs later.’’ The 

commenter states that review of the 

corrosion reports submitted to the 

manufacturer show very few corrosion 

findings on the aft pressure bulkhead. 

The commenter notes that this indicates 

that the Corrosion Prevention and 

Control Program (CPCP) is managing 

corrosion on the bulkhead. The 

commenter adds that periodic corrosion 

findings necessitate doing specific 

inspections; so, due to CPCP 

requirements for similar inspections, 

operators should be able to take credit 

for past inspections per the referenced 

Boeing documents. 

The same commenter asks that the 

repetitive inspections specified in 

paragraph (f) of the proposed rule be 

extended to at least every four years, in 

lieu of every two years. The commenter 

states that the primary difference for the 

aft pressure bulkhead structure between 

the pre-line number 1043 airplanes and 

the post-line number 1043 airplanes is 

the lack of application of corrosion 

inhibiting compound (CIC) on the drain 

holes during manufacture. The 

commenter adds that because the drain 

hole issue is addressed and CICs are 

applied per the proposed rule, 

inspections of all affected airplanes 

should be repeated at the same 4-year 

interval. 

The FAA does not agree with the 

commenter’s requests, as insufficient 

supporting data were provided to us to 

substantiate those requests. In 

developing an appropriate compliance 

time for this action, we considered not 

only the degree of urgency associated 

with addressing the subject unsafe 

condition, but the manufacturer’s 

recommendation as to an appropriate 

compliance time, and the practical 

aspect of accomplishing the required 

inspections within an interval of time 

that parallels normal scheduled 

maintenance for the majority of affected 

operators. 

In addition, the comment stating that 

the primary difference for the aft 

pressure bulkhead structure between the 

pre-line number 1043 airplanes and the 

post-line number 1043 airplanes is the 

lack of application of corrosion 

inhibiting compound (CIC) on the drain 

holes during manufacture is incorrect. 

Post-line number airplanes have 

additional drain hole provisions that 

justify the extended intervals; those 

provisions do not exist for the pre-line 

number airplanes. However, under the 

provisions of paragraph (h)(1) of the 

final rule, we may approve requests for 

adjustments to the compliance time if 

data are submitted to substantiate that 

such an adjustment would provide an 

acceptable level of safety. 

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 as proposed.

36086 Federal Register / Vol. 67, No. 100 / Thursday, May 23, 2002 / Rules and Regulations 

Cost Impact 

There are approximately 2,920 

airplanes of the affected design in the 

worldwide fleet. 

We estimate that 337 airplanes of U.S. 

registry are subject to the existing AD. 

The inspections that are currently 

required by AD 84–20–03 R1 take 

approximately 2 work hours per 

airplane to accomplish, at an average 

labor rate of $60 per work hour. Based 

on these figures, the cost impact of the 

currently required inspections on U.S. 

operators is estimated to be $40,440, or 

$120 per airplane, per inspection cycle.

The drain hole enlargement that is 

currently required by AD 84–20–03 R1 

takes approximately 2 work hours per 

airplane to accomplish, at an average 

labor rate of $60 per work hour. Based 

on these figures, the cost impact of this 

currently required action on U.S. 

operators is estimated to be $40,440, or 

$120 per airplane. 

We estimate that 1,143 airplanes of 

U.S. registry will be affected by this AD. 

The new inspections that are required in 

this AD action will take approximately 

4 work hours per airplane to 

accomplish, at an average labor rate of 

$60 per work hour. Based on these 

figures, the cost impact of these new 

requirements on U.S. operators is 

estimated to be $274,320, or $240 per 

airplane, per inspection cycle. 

The cost impact figures discussed 

above are 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 

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 

removing amendment 39–5183 (50 FR 

51235, December 16, 1985), and by 

adding a new airworthiness directive 

(AD), amendment 39–12757, to read as 

follows:

2002–10–11 Boeing: Amendment 39–12757. 

Docket 2000–NM–359–AD. Supersedes 

AD 84–20–03 R1, Amendment 39–5183.

Applicability: Model 737–100, –200, 

–200C, –300, –400, and –500 series airplanes; 

line numbers (L/N) 1 through 3132 inclusive; 

certificated in any category.

Note 1: This AD applies to each airplane 

identified in the preceding applicability 

provision, regardless of whether it has been 

modified, altered, or repaired in the area 

subject to the requirements of this AD. For 

airplanes that have been modified, altered, or 

repaired so that the performance of the 

requirements of this AD is affected, the 

owner/operator must request approval for an 

alternative method of compliance in 

accordance with paragraph (h)(1) of this AD. 

The request should include an assessment of 

the effect of the modification, alteration, or 

repair on the unsafe condition addressed by 

this AD; and, if the unsafe condition has not 

been eliminated, the request should include 

specific proposed actions to address it.

Compliance: Required as indicated, unless 

accomplished previously. 

To detect and correct corrosion or cracking 

of the aft pressure bulkhead at Body Station 

(BS) 1016, which could result in loss of the 

aft pressure bulkhead web and stiffeners and 

consequent rapid decompression of the 

fuselage, accomplish the following: 

Restatement of Requirements of AD 84–20–

03 R1

Initial Inspection 

(a) For Model 737 series airplanes with L/

N 1 through 929 inclusive, with more than 

20,000 hours time-in-service or 7 years since 

date of manufacture, whichever occurs first: 

Within 120 days after January 20, 1986 (the 

effective date of AD 84–20–03 R1, 

amendment 39–5183), unless already 

accomplished within the 21 months before 

January 20, 1986, visually inspect the BS 

1016 pressure bulkhead for cracking and 

corrosion; according to Boeing Alert Service 

Bulletin 737–53A1075, Revision 1, dated 

September 2, 1983; Revision 2, dated July 13, 

1984; or Revision 3, dated June 8, 2000. 

Remove any obstruction to the drain hole in 

the frame chord and replace any deteriorated 

leveling compound as noted in the service 

bulletin. Treat the area of inspection with 

corrosion inhibitor BMS 3–23, or equivalent. 

Drain Hole Enlargement 

(b) For airplanes identified in paragraph (a) 

of this AD: Within 1 year after January 20, 

1986, accomplish the drain hole enlargement 

as shown in Boeing Alert Service Bulletin 

737–53A1075, Revision 1, dated September 

2, 1983; Revision 2, dated July 13, 1984; or 

Revision 3, dated June 8, 2000. 

Corrective Action 

(c) If cracking or corrosion is found during 

any inspection required by paragraph (a) or 

(d) of this AD, before further flight, repair 

according to paragraph (c)(1) or (c)(2) of this 

AD. 

(1) According to Boeing Alert Service 

Bulletin 737–53A1075, Revision 1, dated 

September 2, 1983; Revision 2, dated July 13, 

1984; or Revision 3, dated June 8, 2000. 

(2) According to 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 (DER) who has 

been authorized by the Manager, Seattle 

ACO, to make such findings. For a repair 

method to be approved by the Manager, 

Seattle ACO, as required by this paragraph, 

the Manager’s approval letter must 

specifically reference this AD. 

Repetitive Inspections 

(d) For airplanes identified in paragraph (a) 

of this AD: Repeat the visual inspections and 

corrosion inhibitor treatment in paragraph (a) 

at intervals not to exceed 2 years, until 

paragraph (e) of this AD has been done. 

New Requirements of This AD 

Initial Inspection 

(e) Do a detailed inspection for cracking or 

corrosion of the aft pressure bulkhead at BS 

1016 (including the forward and aft sides of 

the pressure web, forward and aft sides of the 

pressure chord, pressure chord radius, 

forward and aft sides of the angle stiffener, 

forward and aft chord, stringer end fitting, 

system penetration doublers, channel 

stiffeners and fasteners, ‘‘Z’’ stiffeners and 

fasteners, and fasteners common to the 

pressure chord and pressure web), according

Federal Register / Vol. 67, No. 100 / Thursday, May 23, 2002 / Rules and Regulations 36087

to Boeing Alert Service Bulletin 737–

53A1075, Revision 3, dated June 8, 2000. Do 

this inspection at the applicable time shown 

in paragraph (e)(1), (e)(2), or (e)(3) of this AD.

Note 2: For the purposes of this AD, a 

detailed inspection is defined as: ‘‘An 

intensive visual examination of a specific 

structural area, system, installation, or 

assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at intensity deemed appropriate by 

the inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required.’’

(1) For airplanes on which an inspection 

has previously been done according to the 

requirements of paragraph (a) of this AD: Do 

the inspection within 2 years since the most 

recent inspection according to paragraph (a) 

or (d) of this AD, as applicable. Inspection 

according to paragraph (e) of this AD ends 

the requirement for inspections according to 

paragraph (d) of this AD. 

(2) For airplanes having L/N 930 through 

1042 inclusive, on which an inspection has 

not previously been done according to 

paragraph (a) of this AD: Do the inspection 

within 2 years after the effective date of this 

AD. 

(3) For airplanes having L/N 1043 through 

3132 inclusive, on which an inspection has 

not previously been done according to 

paragraph (a) of this AD: Do the inspection 

within 6 years since the airplane’s date of 

manufacture, or within 2 years after the 

effective date of this AD, whichever occurs 

later. 

Repetitive Inspections 

(f) Repeat the inspection in paragraph (e) 

of this AD at the applicable time shown in 

paragraph (f)(1) or (f)(2) of this AD. 

(1) For airplanes having L/N 1 through 

1042 inclusive: Repeat the inspection at least 

every 2 years. 

(2) For airplanes having L/N 1043 through 

3132 inclusive: Repeat the inspection at least 

every 4 years. 

Repair 

(g) If any corrosion or cracking is found 

during any inspection according to paragraph 

(e) or (f) of this AD: Before further flight, 

repair according to Boeing Alert Service 

Bulletin 737–53A1075, Revision 3, dated 

June 8, 2000. Exception: If corrosion or 

cracking of the web and stiffeners is outside 

the limits specified in the service bulletin, or 

if corrosion or cracking is found in any 

structure not covered by the repair 

instructions in the service bulletin, before 

further flight, repair according to a method 

approved by the Manager, Seattle ACO, or 

per data meeting the type certification basis 

of the airplane approved by a Boeing 

Company DER who has been authorized by 

the Manager, Seattle ACO, to make such 

findings. For a repair method to be approved 

by the Manager, Seattle ACO, as required by 

this paragraph, the Manager’s approval letter 

must specifically reference this AD. 

Alternative Methods of Compliance 

(h)(1) An alternative method of compliance 

or adjustment of the compliance time that 

provides an acceptable level of safety may be 

used if approved by the Manager, Seattle 

ACO. Operators shall submit their requests 

through an appropriate FAA Principal 

Maintenance Inspector, who may add 

comments and then send it to the Manager, 

Seattle ACO. 

(2) Alternative methods of compliance, 

approved previously in accordance with AD 

84–20–03 R1, amendment 39–5183, are 

approved as alternative methods of 

compliance with this AD.

Note 3: Information concerning the 

existence of approved alternative methods of 

compliance with this AD, if any, may be 

obtained from the Seattle ACO.

Special Flight Permits 

(i) Special flight permits may be issued in 

accordance with §§ 21.197 and 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199) to operate the airplane to a 

location where the requirements of this AD 

can be accomplished. 

Incorporation by Reference 

(j) Except as provided by paragraphs (c)(2) 

and (g) of this AD, the actions shall be done 

in accordance with Boeing Alert Service 

Bulletin 737–53A1075, Revision 1, dated 

September 2, 1983; Boeing Alert Service 

Bulletin 737–53A1075, Revision 2, dated July 

13, 1984; or Boeing Alert Service Bulletin 

737–53A1075, Revision 3, dated June 8, 

2000, as applicable. 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 Airplane 

Group, 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 

(k) This amendment becomes effective on 

June 27, 2002.

Issued in Renton, Washington, on May 14, 

2002. 

Vi L. Lipski, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 02–12634 Filed 5–22–02; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2000–NM–394–AD; Amendment 

39–12758; AD 2002–10–12] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–100, –200, –200C, –300, 

–400, and –500 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to all Boeing Model 737–100, 

–200, –200C, –300, –400, and –500 

series airplanes. For certain airplanes, 

this amendment requires a one-time 

inspection or a review of the 

maintenance records of the airplane to 

determine if a particular control rod 

barrel for the aileron tabs is installed, 

and follow-on repetitive inspections for 

cracking of the control rod barrels and 

replacement of the control rod barrels 

with new barrels, if necessary. Such 

replacement terminates the repetitive 

inspections. For all airplanes, this 

amendment prohibits installation of a 

certain control rod barrel for the aileron 

tabs. The actions specified by this AD 

are intended to prevent the 

disconnection of an aileron tab, which 

could lead to severe airframe vibrations; 

consequent damage to the aileron tab, 

aileron, and wing; and possible loss of 

controllability of the airplane. This 

action is intended to address the 

identified unsafe condition.

DATES: Effective June 27, 2002. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of June 27, 

2002.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Boeing Commercial Airplane 

Group, 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: Sue 

Lucier, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2186; 

fax (425) 227–1181.

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 

737–100, –200, –200C, –300, –400, and 

–500 series airplanes was published in 

the Federal Register on September 4, 

2001 (66 FR 46247). For certain 

airplanes, that action proposed to 

require a one-time inspection or a 

review of the maintenance records of 

the airplane to determine if a particular 

control rod barrel for the aileron tabs is