Federal Register / Vol. 60, No. 73 / Monday, April 17, 1995 / Proposed Rules 19179

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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.

Issued in Renton, Washington, on April 11,

1995.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–9345 Filed 4–14–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–183–AD]

Airworthiness Directives; British

Aerospace Model BAC 1–11 200 and

400 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to British

Aerospace Model BAC 1–11 200 and

400 series airplanes, that currently

requires structural inspections and

repairs or replacements, as necessary.

This action would require additional

inspections of certain Structural

Significant Items (SSI) and expansion of

the inspection area for certain other

SSI’s. This proposal is prompted by the

results of a structural integrity audit,

which indicated that in order to

maintain the structural integrity of these

airplanes as they approach or exceed the

manufacturer’s original fatigue design

life goal, certain SSI’s need to be

inspected. The actions specified by the

proposed AD are intended to ensure

continuing structural integrity of these

airplanes.

DATES: Comments must be received by

May 26, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 94–NM–

183–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

British Aerospace, Airbus Limited, P.O.

Box 77, Bristol BS99 7AR, England. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

FOR FURTHER INFORMATION CONTACT:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2148; fax (206) 227–1320.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 94–NM–183–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–03, Attention: Rules Docket No.

94–NM–183–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On September 16, 1988, the FAA

issued AD 87–24–06 R1, amendment

39–6037 (53 FR 37993, September 29,

1988), applicable to British Aerospace

Model BAC 1–11 200 and 400 series

airplanes. That AD requires structural

inspections and repairs or replacements,

as necessary, in order to ensure the

continuing airworthiness of these

airplanes as they approach or exceed the

manufacturer’s original fatigue design

life goal. That action was prompted by

a structural re-evaluation, which

identified certain structurally significant

items (SSI) in which undetected fatigue

cracks could propagate and compromise

the structural integrity of these

airplanes. The requirements of that AD

are intended to ensure continuing

structural integrity of these airplanes.

Since the issuance of that AD, British

Aerospace has conducted a structural

integrity audit to assess the structural

inspection program of Model BAC 1–11

200 and 400 series airplanes. The results

of this audit indicated that, in order to

maintain the structural integrity of these

airplanes as they approach or exceed

85,000 landings (the manufacturer’s

original fatigue design life goal), certain

additional SSI’s need to be inspected

and the inspection area for certain other

SSI’s needs to be expanded.

British Aerospace has issued BAC 1–

11 Alert Service Bulletin 51–A–

PM5830, Issue 4, dated January 28,

1993. This revision of the alert service

bulletin adds ten inspections of the

doors to the structural inspection

program. Some of these inspections

merely expand the area of inspection for

certain SSI’s. Additionally, this revision

of the alert service bulletin describes

procedures for repair or replacement of

cracked parts. Table 3 of the alert

service bulletin specifies life limits for

certain components in the engine

mount/attachment structure of certain

airplanes. The Civil Aviation Authority

(CAA), which is the airworthiness

authority for the United Kingdom, has

classified this revision of the alert

service bulletin as mandatory.

This airplane model is manufactured

in the United Kingdom and is type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the CAA has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the CAA,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, the proposed AD would

supersede AD 87–24–06 R1 to require a

revision of the FAA-approved

maintenance inspection program to
19180 Federal Register / Vol. 60, No. 73 / Monday, April 17, 1995 / Proposed Rules

include additional structural

inspections of certain SSI’s, expansion

of the inspection area for certain other

SSI’s, and repair or replacement of

cracked parts; and establishes a life

limit for the engine mount/attachment

structure on certain airplanes. The

actions would be required to be

accomplished in accordance with the

alert service bulletin described

previously.

However, certain inspections and

repairs specified in the alert service

bulletin have been excluded from the

requirements of this proposal. Those

inspections and repairs have been

identified in the alert service bulletin as

Maintenance Planning Guide (MPG),

Reference Numbers 52–10–6R and 53–

10–2R. The actions specified in MPG

52–10–6R are currently required by AD

87–21–06, amendment 39–5744 (52 FR

38396, October 16, 1987), and those in

MPG 53–10–29R will be addressed in a

separate rulemaking action.

As a result of recent communications

with the Air Transport Association

(ATA) of America, the FAA has learned

that, in general, some operators may

misunderstand the legal effect of AD’s

on airplanes that are identified in the

applicability provision of the AD, but

that have been altered or repaired in the

area addressed by the AD. The FAA

points out that all airplanes identified in

the applicability provision of an AD are

legally subject to the AD. If an airplane

has been altered or repaired in the

affected area in such a way as to affect

compliance with the AD, the owner or

operator is required to obtain FAA

approval for an alternative method of

compliance with the AD, in accordance

with the paragraph of each AD that

provides for such approvals. A note has

been included in this notice to clarify

this long-standing requirement.

The FAA estimates that 31 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 158 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $293,880, or $9,480 per

airplane, per inspection cycle.

The total cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted.

The regulations proposed herein

would not have substantial direct effects

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,

in accordance with Executive Order

12612, it is determined that this

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed 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) if

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

39.13 [Amended]

2. Section 39.13 is amended by

removing amendment 39–6037 (53 FR

37993, September 29, 1988), and by

adding a new airworthiness directive

(AD), to read as follows:

British Aerospace Airbus Limited (Formerly

British Aerospace Commercial Aircraft

Limited, British Aerospace Aircraft

Group): Docket 94–NM–183–AD.

Supersedes AD 87–24–06 R1,

Amendment 39–6037.

Applicability: Model BAC 1–11 200 and

400 series airplanes, 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 use the authority

provided in paragraph (f) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition; or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To ensure continuing structural integrity of

the airplane, accomplish the following:

(a) Within 6 months after November 3,

1988 (the effective date of AD 87–4–06 R1,

amendment 39–6037), incorporate a revision

into the FAA-approved maintenance

inspection program which requires

inspections, repairs, and replacements, as

necessary, in accordance with Tables 1, 2,

and 3 of British Aerospace BAC 1–11 Alert

Service Bulletin 51–A–PM5830, Issue 3,

dated March 19, 1987. The revision to the

maintenance inspection program must

include procedures to notify the

manufacturer when Structural Significant

Items are found cracked or otherwise

significantly deteriorated. Information

collection requirements contained in this

regulation have been approved by the Office

of Management and Budget (OMB) under the

provisions of the Paperwork Reduction Act of

1980 (44 U.S.C. 3501 et seq.) and have been

assigned OMB Control Number 2120–0056.

The inspection thresholds, repetitive

intervals and inspection techniques are listed

in the alert service bulletin.

(b) Within 6 months after the effective date

of this AD, replace the revision of the FAAapproved maintenance inspection program

required by paragraph (a) of this AD, with a

revision which requires inspections, repairs,

and replacements, as necessary, in

accordance with Tables, 1 (except

Maintenance Planning Guide Reference

Numbers 52–10–6R and 53–10–29R), 2, and

3 of British Aerospace BAC 1–11 Alert

Service Bulletin 51–A–PM5830, Issue 4,

dated January 28, 1993. The revision to the

maintenance inspection program must

include procedures to notify the

manufacturer when Structural Significant

Items are found cracked or otherwise

significantly deteriorated. Information

collection requirements contained in this

regulation have been approved by the Office

of Management and Budget (OMB) under the

provisions of the Paperwork Reduction Act of

1980 (44 U.S.C. 3501 et seq.) and have been

assigned OMB Control Number 2120–0056.

The inspection thresholds, repetitive

intervals and inspection techniques are listed

in the alert service bulletin.

Note 2: Maintenance Planning Guide

(MPG) Reference Numbers 52–10–6R and 53–

10–29R, listed in Table 1 of British

Aerospace BAC 1–11 Alert Service Bulletin

51–A–PM5830, Issue 4, dated January 28,

1993, are excluded from the requirements of

this AD for the following reasons:
Federal Register / Vol. 60, No. 73 / Monday, April 17, 1995 / Proposed Rules 19181

MPG reference No. Reason

52–10–6R .... Required by AD 87–21–06,

amendment 39–5744.

53–10–29R .. Will be addressed in a separate rulemaking action.

(c) Within one year after November 3, 1988

(the effective date of AD 87–24–06 R1,

amendment 39–6037), or prior to the

accumulation of the number of landings

listed in the landing threshold indicated in

British Aerospace BAC 1–11 Alert Service

Bulletin 51–A–PM5830, Issue 3, dated March

19, 1987, whichever occurs later, and

thereafter, at intervals not to exceed the

number of landings specified in the alert

service bulletin, accomplish the inspections,

repairs, and replacements, as necessary, of

the Structural Significant Items identified in

Tables 1, 2, and 3 of that service bulletin.

(d) Within one year after the effective date

of this AD, or prior to the accumulation of

the number of landings listed in the landing

threshold indicated in British Aerospace

BAC 1–11 Alert Service Bulletin 51–A–

PM5830, Issue 4, dated January 28, 1993,

whichever occurs later, and thereafter, at

intervals not to exceed the number of

landings specified in the alert service

bulletin, accomplish the inspections, repairs,

and replacements, as necessary, of the

Structural Significant Items identified in

Tables 1 (except Maintenance Planning

Guide Reference Numbers 52–10–6R and 53–

10–29R), 2, and 3 of the alert service bulletin.

Note 3: For operators that have

accomplished this inspection previously in

accordance with the requirements of AD 87–

24–06 R1, amendment 39–6037: This

paragraph requires that the next scheduled

inspection for that SSI be performed within

the repetitive interval specified for that SSI

in the alert service bulletin after the last

inspection performed in accordance with the

requirements of AD 87–24–06 R1 for that SSI.

(e) For any cracked structure detected

during any inspection required by this AD,

prior to further flight, accomplish paragraph

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

(1) Replace the cracked part with a

serviceable part of the same part number, in

accordance with the Airplane Maintenance

Manual. Or

(2) Repair the cracked structure in

accordance with the Structural Repair

Manual, listed in the service bulletin. Or

(3) Repair in accordance with a method

approved by the Manager, Standardization

Branch, ANM–113, FAA, Transport Airplane

Directorate.

(f) 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,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(g) 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.

Issued in Renton, Washington, on April 11,

1995.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–9347 Filed 4–14–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–40–AD]

Airworthiness Directives; Boeing

Model 737 Series Airplanes Equipped

With BFGoodrich Main Landing Gear

Brake Assemblies

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Boeing Model 737 series

airplanes. This proposal would require

inspection of certain brake assemblies to

determine the part number of the torque

plates, measurement of the amount of

wear remaining on the brake wear pin

indicator, and removal of brake

assemblies on which misidentified

torque plates were installed and

replacement with serviceable brakes.

This proposal is prompted by a report

that certain torque plates were

misidentified and installed on certain

brake assemblies. The actions specified

by the proposed AD are intended to

prevent decreased brake performance

during a rejected takeoff or landing

when these brakes are at or near their

indicated wear limit. (The brake wear

pin indicator would falsely indicate

longer remaining wear because of the

misidentified longer torque plates that

were installed on these brake

assemblies.)

DATES: Comments must be received by

May 11, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 95–NM–

40–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

BFGoodrich Aerospace, Aircraft Wheels

and Brakes, P.O. Box 340, Troy, Ohio

45373. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

David M. Herron, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130S, FAA, Transport Airplane

Directorate, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2672; fax (206) 227–1181.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 95–NM–40–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–103, Attention: Rules Docket No.

94–NM–40–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

Recently, BFGoodrich shipped some

torque plates that were misidentified as