- Effective
- December 30, 1998
- Published
- November 25, 1998 · 63 FR 65045–65047
- Models
- 188A, 188C
- Data sheet
- TCDS4A22
- Registered aircraft
- 4 matched by model
- Product
- Aircraft · Large airplane
- Amendment
- 39-10911
- Docket
- 98-NM-84-AD
- Issued as
- Final rule
Unofficial copy of the text in the FAA’s Dynamic Regulatory System. Only the govinfo PDF is the legal edition. DRS record last changed May 30, 2024.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
| File | Size | SHA-256 | Original |
|---|---|---|---|
| Official PDF | 126 KB | 402676d3…5a57b7d | 98-31319.pdf on govinfo.gov |
| FAA DRS HTML | 62 KB | 8881426c…4a2fd92 | FAA DRS (API key needed) |
| Federal Register text | 16 KB | d6d3a6fa…80a3aa9 | 98-31319.txt on federalregister.gov |
On this page
Summary
This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model L-188A and L-188C series airplanes, that requires revising the Airplane Flight Manual to provide the flightcrew with modified procedures and limitations for operating in icing conditions. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines that experienced tailplane stall due to ice accretion on the horizontal stabilizer of the airplane. The actions specified by this AD are intended to prevent undetected accretion of ice on the horizontal stabilizer, which could result in ice contaminated tailplane stall and consequent loss of pitch control.
The airworthiness directive
98-24-25 LOCKHEED: Amendment 39-10911. Docket 98-NM-84-AD.
Applicability: All Model L-188A and L-188C 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 (b) 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 undetectedaccretion of ice on the horizontal stabilizer, which could result in ice contaminated tailplane stall and consequent loss of pitch control, accomplish the following:
(a) Within 30 days after the effective date of this AD, revise the Limitations, Normal Procedures, and Performance Sections and Appendix III of the FAA-approved Electra 188A or 188C Airplane Flight Manual (AFM), as applicable, to include the pages specified in Table 1 (for Model L-188A series airplanes), Table 2 (for Model L-188C series airplanes not equipped with Hamilton Standard propellers), or Table 3 (for Model L-188C series airplanes equipped with Hamilton Standard propellers) of this AD, as applicable.
Table 1. Revisions to the Electra 188A AFM for all Model L-188A series airplanes
Section Number
Section
Page Number Date Shown on Page Preface Log of Pages i March 10, 1998 Preface Log of Pages ii March 10, 1998 1 Limitations 6 December 1, 1997 3 Normal Procedures 10.1 December 1, 1997 3 Normal Procedures 11 March 10, 1998 3 Normal Procedures 12 December 1, 1997 4 Performance A December 1, 1997 4 Performance 6 December 1, 1997 4 Performance 8 December 1, 1997 4 Performance 12 December 1, 1997 4 Performance 12.1 December 1, 1997 4 Performance 12.2 December 1, 1997 Appendix III Alt. Flap Data B December 1, 1997
Table 2. Revisions to the Electra 188C AFM for Model L-188C series airplanes not equipped with Hamilton Standard propellers
Section Number
Section
Page Number Date Shown on Page Preface Log of Pages i March 10, 1998 Preface Log of Pages ii March 10, 1998 1 Limitations 6 December 1, 1997 3 Normal Procedures 12.1 December 1, 1997 3 Normal Procedures 13 March 10, 1998 3 Normal Procedures 14 December 1, 1997 4 Performance A December 1, 1997 4 Performance 6 December 1, 1997 4 Performance 8 December 1, 1997 4 Performance 12 December 1, 1997 4 Performance 12.1 December 1, 1997 4 Performance 12.2 December 1, 1997 Appendix III Alt. Flap Data B December 1, 1997
Table 3. Revisions to the Electra 188C AFM for Model L-188C series airplanes equipped with Hamilton Standard propellers
Section Number
Section
Page Number Date Shown on Page Preface Log of Pages i March 10, 1998 Preface Log of Pages ii March 10, 1998 1 Limitations 6 December 1, 1997 3 Normal Procedures 12.1 December 1, 1997 3 Normal Procedures 13 March 10, 1998 3 Normal Procedures 14 December 1, 1997 A4 Performance A December 1, 1997 A4 Performance 6 December 1, 1997 A4 Performance 8 December 1, 1997 A4 Performance 12 December 1, 1997 A4 Performance 12.1 December 1, 1997 A4 Performance 12.2 December 1, 1997 Appendix AIII Alt. Flap Data B December 1, 1997
(b) 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, Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Operations Inspector, who may add comments and then send it to the Manager, Atlanta ACO.
NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO.
(c) 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.
(d) The AFM revisions shall be done in accordance with the following Lockheed Airplane Flight Manuals, which contain the specified list of effective pages:
Airplane Flight Manuals
Page Number Date Shown on Page Electra Model 188A March 10, 1998 Log of PagesPages i through Jii March 10, 1998 Electra Model 188C March 10, 1998 Log of Pages Pages i through Lii March 10, 1998
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 Lockheed Aeronautical Systems Support Company (LASSC), Field Support Department, Dept. 693, Zone 0755, 2251 Lake Park Drive, Smyrna, Georgia 30080. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(e) This amendment becomes effective on December 30, 1998.
Rule preamble
The FAA’s background, reasoning and cost estimate, published with the AD.
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 Lockheed Model L-188A and L-188C series airplanes was published in the Federal Register on August 13, 1998 (63 FR 43340). That action proposed to require revising the Airplane Flight Manual to provide the flightcrew with modified procedures and limitations for operating in icing conditions. Comments Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the single comment received.
The commenter supports the proposed rule.
Conclusion After careful review of the available data, including the comment noted above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed.
Cost Impact There are approximately 75 airplanes of the affected design in the worldwide fleet. The FAA estimates that 32 airplanes of U.S. registry will be affected by this AD, that it will take approximately 1 work hour per airplane to accomplish the required incorporation of the AFM revisions, and that the average labor rate is $60 per work hour. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $1,920, or $60 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.
Regulatory Impact The regulations adopted herein will 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 final rule does nothave sufficient federalism implications to warrant the preparation of a Federalism Assessment.
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 39of 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:
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 4
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1959 | 2 |
|---|---|
| 1960 | 1 |
1 with no year recorded