19682 Federal Register / Vol. 63, No. 76 /Tuesday, April 21, 1998 / Proposed Rules

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. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

British Aerospace Regional Aircraft

[Formerly Jetstream Aircraft Limited;

British Aerospace (Commercial Aircraft)

Limited]: Docket 98–NM–86–AD.

Applicability: Jetstream Model 4100

airplanes, constructor’s numbers 41004

through 41096 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 (c) 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 correct corrosion of the upper splice

plate of the wing, which could result in

reduced structural integrity of the airplane,

accomplish the following:

(a) Within 6 months after the effective date

of this AD, perform an eddy current

conductivity test to measure the conductivity

of the upper splice plate of the wing, in

accordance with British Aerospace Regional

Aircraft Service Bulletin J41–57–019,

Revision 1, dated November 26, 1997,

including Appendix 1. If the conductivity

measurement is greater than or equal to

35.0% of the International Aluminum and

Copper Standards (IACS), no further action is

required by this AD.

(b) During the inspection required by

paragraph (a) of this AD, if the conductivity

measurement is less than 35.0% of the IACS:

Prior to further flight, use a boroscope to

perform a detailed visual inspection to detect

corrosion along the full length of the upper

splice plate of the wing, in accordance with

British Aerospace Regional Aircraft Service

Bulletin J41–57–020, dated March 20, 1997,

including Appendix 1 and Appendix 2.

Thereafter, repeat the inspection at intervals

not to exceed 1 year.

(1) During any inspection required by

paragraph (b) of this AD, if any corrosion is

detected that is within the allowable limits

specified in the service bulletin: Accomplish

the actions required by paragraphs (b)(1)(i)

and (b)(1)(ii) of this AD, at the times

specified in those paragraphs.

(i) Prior to further flight, repair the upper

splice plate of the wing in accordance with

Appendix 2 of the service bulletin. And

(ii) Within 3 years after the detection of

corrosion, replace the upper splice plate of

the wing with a new upper splice plate in

accordance with the service bulletin. Such

replacement constitutes terminating action

for the requirements of this AD.

(2) During any inspection required by

paragraph (b) of this AD, if any corrosion is

detected that is outside the allowable limits

specified in the service bulletin: Prior to

further flight, repair in accordance with a

method approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate.

(c) 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,

International Branch, ANM–116. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(d) 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.

Note 3: The subject of this AD is addressed

in British airworthiness directive 005–03–97

(undated).

Issued in Renton, Washington, on April 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–10483 Filed 4–20–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–51–AD]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace BAC 1–11 200 and 400

Series Airplanes

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 all

British Aerospace Model BAC 1–11 200

and 400 series airplanes. This proposal

would require repetitive detailed visual

inspections to detect cracking in the

trunnion fittings located in the nose

landing gear (NLG) bay of the forward

fuselage; and repair, if necessary. This

proposal is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by the proposed AD are

intended to detect and correct cracking

in the trunnion fittings of the NLG,

which could lead to collapse of the NLG

during takeoff and landing, and possible

injury to the flight crew and passengers.

DATES: Comments must be received by

May 21, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

51–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, Service Support,

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:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION:
Federal Register / Vol. 63, No. 76 /Tuesday, April 21, 1998 / Proposed Rules 19683

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 98–NM–51–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–114, Attention: Rules Docket No.

98–NM–51–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Civil Aviation Authority (CAA),

which is the airworthiness authority for

the United Kingdom, notified the FAA

that an unsafe condition may exist on

all British Aerospace Model BAC 1–11

200 and 400 series airplanes. The CAA

advises that operators have reported

cracks in the trunnion fittings located in

the nose landing gear (NLG) bay on the

forward fuselage. The cracks propagated

through the material thickness in the

area of the trunnion cap attachment

holes, on both the left- and right-hand

trunnion fittings. Laboratory

examination indicates that the damage

to the trunnion fittings is characteristic

of stress corrosion cracking.

Additionally, service experience has

indicated that certain BAC 1–11 200 and

400 series airplanes on which British

Aerospace Modification 5308 has been

accomplished may be more prone to

such cracking and, therefore, a more

stringent inspection schedule is

required for these airplanes. (British

Aerospace Modification 5308 introduces

new bearing assemblies and trunnion

caps, and strengthening of associated

components.) Such cracking in the

trunnion fittings, if not detected and

corrected, could lead to collapse of the

NLG during takeoff and landing, and

possible injury to the flight crew and

passengers.

Explanation of Relevant Service

Information

British Aerospace has issued Alert

Service Bulletin 53–A–PM6035,

Revision 1, dated March 7, 1996, which

describes procedures for repetitive

detailed visual inspections to detect

cracking on the left- and right-hand

trunnion fittings of the NLG in the area

of the trunnion cap attachment holes on

both the inner and outer faces of the

fitting. The CAA classified this alert

service bulletin as mandatory and

issued British airworthiness directive

004–03–96, dated April 26, 1996, in

order to assure the continued

airworthiness of these airplanes in the

United Kingdom.

FAA’s Conclusions

This airplane model is manufactured

in the United Kingdom and is type

certificated for operation in the United

States under the provisions of § 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.

Explanation of Requirements of

Proposed Rule

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 require

accomplishment of the actions specified

in the alert service bulletin described

previously. The actions would be

required to be accomplished in

accordance with the alert service

bulletin described previously, except as

discussed below.

Differences Between Proposed Rule and

Service Bulletin

Operators should note that, although

the alert service bulletin specifies that

the manufacturer may be contacted for

repairing crack conditions, this proposal

would require the repair of those

conditions to be accomplished in

accordance with a method approved by

the FAA.

Cost Impact

The FAA estimates that 42 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 1 work hour per airplane

to accomplish the proposed inspection,

and that the average labor rate is $60 per

work hour. Based on these figures, the

cost impact of the proposed AD on U.S.

operators is estimated to be $2,520, or

$60 per airplane.

The 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.

Regulatory Impact

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:
19684 Federal Register / Vol. 63, No. 76 /Tuesday, April 21, 1998 / Proposed Rules

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:

British Aerospace Airbus Limited (Formerly

British Aerospace Commercial Aircraft

Limited, British Aerospace Aircraft

Group): Docket 98–NM–51–AD.

Applicability: All 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 request approval for an

alternative method of compliance in

accordance with paragraph (c) 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 cracking in the

trunnion fittings of the nose landing gear

(NLG), which could lead to collapse of the

NLG during takeoff and landing, and possible

injury to the flight crew and passengers,

accomplish the following:

(a) Perform a detailed visual inspection for

cracking on the left- and right-hand trunnion

fittings of the NLG, in the area of the

trunnion cap attachment holes, in accordance

with British Aerospace Alert Service Bulletin

53–A–PM6035, Revision 1, dated March 7,

1996; at the time specified in paragraph (a)(1)

or (a)(2) of this AD, as applicable.

(1) For airplanes on which British

Aerospace Modification PM5308 has not

been accomplished: Perform the inspection

within 6 years after the effective date of this

AD, or within 11 years after the last

inspection accomplished in accordance with

the alert service bulletin, whichever occurs

later. Repeat the inspection thereafter at

intervals not to exceed 11 years.

(2) For airplanes on which British

Aerospace Modification PM5308 has been

accomplished: Perform the inspection within

30 months after the effective date of this AD,

or within 5 years after the last inspection

accomplished in accordance with the alert

service bulletin, whichever occurs later.

Repeat the inspection thereafter at intervals

not to exceed 6 years.

(b) If any crack is found during any

inspection required by paragraph (a) of this

AD, prior to further flight, repair the crack in

accordance with a method approved by the

Manager, International Branch, ANM–116,

FAA, Transport Airplane Directorate.

(c) 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,

International Branch, ANM–116. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(d) 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.

Note 3: The subject of this AD is addressed

in the British airworthiness directive 004–

03–96, dated April 26, 1996.

Issued in Renton, Washington, on April 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–10475 Filed 4–20–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–81–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300 and A300–600 Series Airplanes

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 Airbus Model A300 and all

Model A300–600 series airplanes. This

proposal would require a one-time

inspection for cracking of the gantry

lower flanges in the main landing gear

(MLG) bay area; and repair, if necessary.

This proposal is prompted by issuance

of mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by the proposed AD are

intended to detect and correct cracking

of the gantry lower flanges in the MLG

bay area, which could result in

decompression of the airplane.

DATES: Comments must be received by

May 21, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

81–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

Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

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 98–NM–81–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