Federal Register / Vol. 66, No. 35 / Wednesday, February 21, 2001 / Rules and Regulations 10953

estimates the cost impact of the

replacement to be $5,289 per airplane.

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

adding the following new airworthiness

directive:

2001–03–10 Boeing: Amendment 39–12114.

Docket 99–NM–206–AD.

Applicability: All Model 747–100, –100B,

–100B SUD, –200B, –200C, –200F, –300,

–400, –400D, –400F, and 747SR 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 prevent loss of a flap transmission,

which could reduce lateral controllability of

the airplane, accomplish the following:

Replacement

(a) Except as provided by paragraph (b) of

this AD, within 18 months after the effective

date of this AD, perform a one-time general

visual inspection to determine whether H–11

steel bolts are installed as attach and support

bolts at the trailing edge flap transmissions,

in accordance with Boeing Alert Service

Bulletin 747–27A2376, dated July 1, 1999.

(1) If no H–11 steel bolt is found, no further

action is required by this AD.

(2) If any H–11 steel bolt is found, before

further flight, replace with an Inconel bolt, in

accordance with the alert service bulletin.

Note 2: 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 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.’’

Alternative Inspection for Certain Airplanes

(b) For airplanes having line number (L/N)

872 and subsequent: Instead of doing

paragraph (a) of this AD, it is acceptable to

inspect airplane maintenance records to

determine if a flap transmission or flap track

repair or replacement has been done. This

inspection of the maintenance records, if

done, is required at the same 18-month

compliance time as the inspection required

by paragraph (a) of this AD.

(1) If no flap transmission or flap track

repair or replacement has been done: No

further action is required by this AD.

(2) If any flap transmission or flap track

repair or replacement has been done, or if it

cannot be determined from the inspection of

the maintenance records if such repair or

replacement has been done: Within 18

months after the effective date of this AD, do

paragraph (a) of this AD.

Alternative Methods of Compliance

(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, Seattle

Aircraft Certification Office (ACO), FAA.

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.

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

(d) Special flight permits may be issued in

accordance with sections 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

(e) Except as provided by paragraph (b) of

this AD, the actions shall be done in

accordance with Boeing Alert Service

Bulletin 747–27A2376, dated July 1, 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 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

(f) This amendment becomes effective on

March 28, 2001.

Issued in Renton, Washington, on February

8, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–3699 Filed 2–20–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–224–AD; Amendment

39–12116; AD 2001–03–12]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace (Jetstream) Model 4101

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to all British Aerospace

(Jetstream) Model 4101 airplanes, that

currently requires repetitive inspections

to detect loose or migrated levers of the

elevator cable tension regulators, and

replacement of the regulator assembly

with a new assembly, if necessary. This

amendment requires modification of the

elevator cable tension regulator lever

assembly, terminating the repetitive

inspections. This amendment is

10954 Federal Register / Vol. 66, No. 35 / Wednesday, February 21, 2001 / Rules and Regulations

prompted by issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified by this AD are

intended to prevent the elevator cable

tension regulator from becoming

detached from the splined shaft of the

assembly, which could result result in

difficulty adjusting the elevators,

leading to reduced controllability of the

airplane.

DATES: Effective March 28, 2001.

The incorporation by reference of

Jetstream Service Bulletin J41–27–059,

dated May 31, 2000, as listed in the

regulations, is approved by the Director

of the Federal Register as of March 28,

2001.

The incorporation by reference of

Jetstream Alert Service Bulletin J41–A–

27–053, dated September 14, 1999, as

listed in the regulations, was approved

previously by the Director of the Federal

Register as of February 1, 2000 (64 FR

72531, December 28, 1999).

ADDRESSES: The service information

referenced in this AD may be obtained

from British Aerospace Regional

Aircraft American Support, 13850

Mclearen Road, Herndon, Virginia

20171. 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: Dan

Rodina, Aerospace Engineer, ANM–116,

FAA, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2125; fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 99–26–18,

amendment 39–11478 (64 FR 72531,

December 28, 1999), which is applicable

to all British Aerospace (Jetstream)

Model 4101 airplanes, was published in

the Federal Register on December 5,

2000 (65 FR 75879). The action

proposed to continue to require

repetitive inspections to detect loose or

migrated levers of the elevator cable

tension regulators, and replacement of

the regulator assembly with a new

assembly, if necessary. The action also

proposed to require modification of the

elevator cable tension regulator lever

assembly, terminating the repetitive

inspections.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 57 airplanes

of U.S. registry that will be affected by

this AD. The repetitive inspection that

is currently required by AD 99–26–18

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 the

currently required actions on U.S.

operators is estimated to be $120 per

airplane, per inspection cycle.

The modification that is required in

this AD will take approximately 6 work

hours per airplane to accomplish at an

average labor rate of $60 per work hour.

There will be no charge for required

parts. Based on these figures, the cost

impact of the requirements of this AD

on U.S. operators is estimated to be

$20,520, or $360 per airplane.

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 39–11478 (64 FR

72531, December 28, 1999), and by

adding a new airworthiness directive

(AD), amendment 39–12116, to read as

follows:

2001–03–12 British Aerospace Regional

Aircraft (Formerly Jetstream Aircraft

Limited British Aerospace (Commercial

Aircraft) Limited): Amendment 39–

12116. Docket 2000–NM–224–AD.

Supersedes AD 99–26–18, Amendment

39–11478.

Applicability: All Model Jetstream 4101

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 (e) 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 prevent the elevator cable tension

regulators from becoming detached from the

splined shaft of the assembly, which could

result in difficulty adjusting the elevators,

leading to reduced controllability of the

airplane, accomplish the following:

Federal Register / Vol. 66, No. 35 / Wednesday, February 21, 2001 / Rules and Regulations 10955

Restatement of Certain Actions Required by

AD 99–26–18

Inspection

(a) Within 7 weeks after February 1, 2000

(the effective date of AD 99–26–18,

amendment 39–11478), perform a detailed

visual inspection of the elevator cable

tension regulator lever assembly to detect

discrepancies (including looseness and

migration along the splines of the elevator

cable tension regulator assembly), in

accordance with Jetstream Alert Service

Bulletin J41–A–27–053, dated September 14,

1999. Repeat the inspection thereafter at

intervals not to exceed 1,500 flight hours

until accomplishment of paragraph (c) of this

AD.

Note 2: For the purposes of this AD, a

detailed visual 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.’’

New Actions Required by This AD

Modification

(b) If any discrepancy is detected during

any inspection required by paragraph (a) of

this AD: Prior to further flight, perform the

requirements of paragraph (c) of this AD.

(c) Except as required by paragraph (b) of

this AD: Within 12 months after the effective

date of this AD, modify the elevator cable

tension regulators in accordance with

Jetstream Service Bulletin J41–27–059, dated

May 31, 2000.

(d) As of the effective date of this AD, no

person shall install any elevator cable tension

regulator lever assembly, unless that

assembly has been modified in accordance

with the requirements of paragraph (c) of this

AD.

Alternative Methods of Compliance

(e) 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, 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, International Branch,

ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(f) Special flight permits may be issued in

accordance with sections 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

(g) The actions shall be done in accordance

with Jetstream Alert Service Bulletin J41–A–

27–053, dated September 14, 1999; and

Jetstream Service Bulletin J41–27–059, dated

May 31, 2000; as applicable.

(1) This incorporation by reference of

Jetstream Service Bulletin J41–27–059, dated

May 31, 2000, 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

Jetstream Alert Service Bulletin J41–A–27–

053, dated September 14, 1999, was

approved previously by the Director of the

Federal Register as of February 1, 2000 (64

FR 72531, December 28, 1999).

(3) Copies may be obtained from British

Aerospace Regional Aircraft American

Support, 13850 Mclearen Road, Herndon,

Virginia 20171. 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.

Note 4: The subject of this AD is addressed

in British airworthiness directive 006–05–

2000.

Effective Date

(h) This amendment becomes effective on

March 28, 2001.

Issued in Renton, Washington, on February

8, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–3696 Filed 2–20–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–CE–54–AD; Amendment

39–12115; AD 2001–03–11]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace HP137 Mk1, Jetstream

Series 200, and Jetstream Models 3101

and 3201 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to all British Aerospace HP137

Mk1, Jetstream series 200, and Jetstream

Models 3101 and 3201 airplanes that are

equipped with certain main landing

gear (MLG) radius rods. This AD

requires inspection of the MLG radius

rods for cracks and replacement of any

cracked rod. This AD is the result of

mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for the United

Kingdom. The actions specified by this

AD are intended to detect and correct

cracks in the MLG radius rods. Such

cracks could result in MLG failure

during takeoff, landing, or taxi

operations, with consequent loss of

airplane control.

DATES: This AD becomes effective on

April 6, 2001.

The Director of the Federal Register

approved the incorporation by reference

of certain publications listed in the

regulations as of April 6, 2001.

ADDRESSES: You may get the service

information referenced in this AD from

British Aerospace Regional Aircraft,

Prestwick International Airport,

Ayrshire, KA9 2RW, Scotland;

telephone: (01292) 479888; facsimile:

(01292) 479703. You may examine this

information at the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 2000–CE–

54–AD, 901 Locust, Room 506, Kansas

City, Missouri 64106; or at the Office of

the Federal Register, 800 North Capitol

Street, NW, suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Doug Rudolph, Aerospace Engineer,

FAA, Small Airplane Directorate, 901

Locust, Room 301, Kansas City,

Missouri 64106; telephone: (816) 329–

4059; facsimile: (816) 329–4090.

SUPPLEMENTARY INFORMATION:

Discussion

What events have caused this AD?

The Civil Aviation Authority (CAA),

which is the airworthiness authority for

the United Kingdom, recently notified

the FAA that an unsafe condition may

exist on certain British Aerospace

HP137 Mk1, Jetstream series 200, and

Jetstream Models 3101 and 3201

airplanes. The CAA reports an incident

where a MLG radius rod cylinder

cracked, which allowed the gland nut to

separate from the housing and caused

the MLG unit to move 30 degrees

outboard.

The cause has been traced to a quality

control problem with the MLG

manufacturer, APPH Ltd. In particular,

the cause is inadequate countersinking

of a drilled hole for the attachment of

a flexible hose on a batch of MLG radius

rods, part numbers 1847 and 1862, all

suffixes.

What are the consequences if the

condition is not corrected? Cracks in the

MLG radius rods, if not detected and

corrected, could result in MLG failure

during takeoff, landing, or taxi

operations, with consequent loss of

airplane control.